[Federal Register Volume 64, Number 229 (Tuesday, November 30, 1999)]
[Rules and Regulations]
[Pages 66747-66752]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30519]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-87-AD; Amendment 39-11434; AD 99-24-10]
RIN 2120-AA64
Airworthiness Directives; Precise Flight, Inc. Model SVS III
Standby Vacuum Systems
AGENCY: Federal Aviation Administration, DOT.
[[Page 66748]]
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all aircraft equipped with Precise Flight, Inc. Model SVS
III standby vacuum systems installed in accordance with the applicable
supplemental type certificate (STC) or through field approval. This AD
requires incorporating revised operating limitations for the affected
standby vacuum systems into the airplane flight manual (AFM), and
repetitively inspecting the push-pull cable, vacuum lines, saddle
fittings, and shuttle valve for correct installation and damage (wear,
chafing, deterioration, etc.). This AD also requires immediately
correcting any discrepancy found and conducting a function test of the
vacuum system after the inspections. This AD is the result of reports
of shuttle valve failure and standby vacuum system malfunction on
aircraft. The actions specified by this AD are intended to detect and
correct problems with the standby vacuum system before failure or
malfunction and to provide operating procedures for the pilot regarding
the use and limitations of this system.
DATES: Effective January 14, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 14, 2000.
ADDRESSES: Service information that applies to this AD may be obtained
from Precise Flight, Inc., 63120 Powell Butte Road, Bend, Oregon 97701;
telephone: (800) 547-2558. This information may also be examined at the
Federal Aviation Administration (FAA), Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 98-CE-87-AD, 901 Locust,
Room 506, Kansas City, Missouri 64106; or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ms. Dorothy Lundy, Aerospace Engineer,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW,
Renton, Washington 98055-4065; telephone: (425) 227-2260; facsimile:
(425) 227-1181.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to all aircraft equipped
with Precise Flight, Inc. Model SVC III standby vacuum systems
installed in accordance with the applicable supplemental type
certificate (STC) or through field approval was published in the
Federal Register as a notice of proposed rulemaking (NPRM) on July 7,
1999 (64 FR 36618). The NPRM proposed to require incorporating revised
operating limitations for the affected standby vacuum systems into the
airplane flight manual (AFM), and repetitively inspecting the push-pull
cable, vacuum lines, saddle fittings, and shuttle valve for correct
installation and damage (wear, chafing, deterioration, etc.). The NPRM
also proposed to require immediately correcting any discrepancy found
and conducting a function test of the vacuum system after each
inspection.
The NPRM was the result of reports of shuttle valve failure and
standby vacuum system malfunction on aircraft.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Compliance Time of This AD
The compliance times of this AD are presented in calendar time.
Although malfunction or failure of the standby vacuum systems is only
unsafe while the aircraft is in flight, the condition is not a direct
result of repetitive aircraft operation. The unsafe condition could
exist on a standby vacuum system installed on an aircraft with only 50
hours time-in-service (TIS), but may not develop on another standby
vacuum system installed on an aircraft until 1,000 hours TIS. The
inspection compliance times are utilized to coincide with annual
inspections so as to allow the owner/operator of the aircraft to have
the required action accomplished at a time when he/she has already
scheduled maintenance activities.
Cost Impact
The FAA estimates that 10,000 standby vacuum systems will be
affected by this AD, that it will take approximately 3 workhours per
vacuum system to accomplish the actions, and that the average labor
rate is approximately $60 an hour. Based on these figures, the total
cost impact of this AD on U.S. operators is estimated to be $1,800,000,
or $180 per airplane.
These figures only take into account the costs of the initial
inspection and initial functional test of the standby vacuum systems;
subsequent inspections and functional tests and any corrective actions
are not included in the cost impact. The FAA has no way of determining
the number of repetitive inspections and functional tests each airplane
owner/operator will incur over the life of an airplane incorporating
one of the affected standby vacuum systems. The FAA also has no way of
determining the number of standby vacuum systems that will require
corrective action based on the inspection results.
Regulatory Impact
This rule does not have Federalism implications as defined in
Executive Order No. 13132. This means it does not have substantial
direct effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. The FAA has
not consulted with state authorities prior to publication of this rule.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
[[Page 66749]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
99-24-10 Precise Flight, Inc.: Amendment 39-11434; Docket No. 98-CE-
87-AD.
Applicability: Model SVS III standby vacuum systems, installed
on, but not limited to, the aircraft listed in the following chart.
These systems can be installed either in accordance with the
applicable supplemental type certificate (STC) or through field
approval:
----------------------------------------------------------------------------------------------------------------
Affected STC Make and model airplanes
----------------------------------------------------------------------------------------------------------------
SA2160NM............................................ Raytheon Beech Models 23, A23, A23A, A23-19, 19A, B19,
B19A, A23-24, B23, C23, A24, A24R, B24R, C24R, 35, A35,
B35, C35, D35, E35, F35, G35, 35R, H35, J35, K35, M35,
N35, P35, S35, V35, V35A, V35B, 35-33, 35-A33, 35-B33, 35-
C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, G33, 36,
A36, A36TC, B36TC, 4S (YT-34), A45 (T-34A, B-45), D45(T-
34B), and 77 Series.
SA2161NM............................................ Raytheon Beech Model V35B.
SA2162NM............................................ Cessna Models 120, 140, 140A, 150, 150A, 150B, 150C, 150D,
150E, 150F, 150G, 150H, 150J, 150K, 150L, A150L, 150M,
152, A152, A150K, A150M, 170, 170A, 170B, 172, 172A,
172B, 172C, 172D, 172E, 172F (USAFT-41A), 172G, 172H
(USAFT-41A), 172I, 172K, 172L, 172M, 172N, 172P, 172Q,
175, 175A, 175B, 175C, P172D, R172E (USAFT-41B, USAFT41-
3, and USAFT-41D), R172F (USAFT-41D and USAFT-41C), R172G
(USAFT-41D), R172H (USAFT-41D), R172J, R172K, 172RG, 177,
177A, 177B, 177RG, 180, 180A, 180B, 180C, 180D, 180E,
180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C,
182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M,
182N, 182P, 182Q, 182R, 182RG, T182, T182RG, T182R, 185,
185A, 185B, 185C, 185D, 185E, A185E, A185F, 188, 188A,
188B, A188, A188B, T188C, 206, P206, P206A, P206B, P206C,
P206D, P206E, TP206A, TP206B, TP206C, TP206D. TP206E,
U206-A, U206-B, U206-C, U206-D, U206-E, U206-F, U206G,
TU206-A, TU206-B, TU206-C, TU206-D, TU206-E, TU206-F,
TU206-G, 207, 207A, T207, T207A, 210, 210A, 210B, 210C,
210D, 210E, 210F, 210-5 (205), 210-5A (205A), T210F,
210G, T-210G, 210H, T-210H, 210J, 205P, T-210J, 210K, T-
210K, T210L, 210L, 210M, T210M, 210N, P210N, T210N, 205T,
210R, P210R, 205U, T210R, 210-5, 210-5A, 305A (USAF 0-
1A), 305C (USAF 0-1E), 305D (USAF 0-1F), 305F, 305B (USAF
T0-1D), 305E (0-1D or 0-1F), and 321 (Navy 0E-2).
SA2163NM............................................ Cessna Model U206G.
SA2164NM............................................ Cessna Model 180Q.
SA2166NM............................................ Cessna Model 177.
SA2167NM............................................ The New Piper Aircraft, Inc. (Piper) Models L-14, PA-12,
PA-12S, PA-14, PA-15, PA-16, PA-16S, PA-17, PA-18, PA-
18A, PA-18S, PA-18-105 (Special), PA-18S-105 (SP), PA-18-
125 (Army L-21A), PA-18AS-125, PA-18S-125, PA-18-135, PA-
18A-135, PA-18AS-135, PA-18S-135, PA-18-150, PA-18A-150,
PA-18AS-150, PA-18S-150, PA-19 (Army L-18C), PA-19S, PA-
20, PA-20S, PA-20-115, PA-20S-115, PA-20-135, PA-22, PA-
22-108, PA-22-135, PA-22S-135, PA-22-150, PA-22S-150, PA-
22-160, PA-22S-160, PA-24, PA-24-250, PA-24-260, PA-24-
400, PA-25, PA-25-235, PA-25-260, PA-32-260, PA-32RT-300,
PA-32RT-301T, PA-32-300, PA-32RT-300T, PA-32-301, PA-32S-
300, PA-32R-301, PA-32-301T, PA-32R-300, PA-32R-301T, PA-
28-140, PA-28-141, PA-28-150, PA-28-151, PA-28-160, PA-
28S-160, PA-28-180, PA-28R-180, PA-28S-180, PA-28-235, PA-
28S-235, PA-28-181, PA-28-161, PA-28R-200, PA-28R-201, PA-
28R-201T, PA-28-236, PA-28RT-201, PA-28RT-201T, PA-28-
201T, PA-36-285, PA-36-300, PA-36-375, PA-38-112, and PA-
46-310P.
SA2168NM............................................ Mooney Models M20, M20A, M20B, M20C, M20D, M20E, M20F,
M20G, M20J, M20K, M20M, and M22.
[[Page 66750]]
SA2683NM............................................ Aerocar, Inc. Model I, Aerodifusion, S.L. Model Jodel D-
1190S, Aeromere, S.A. Model Falco F.8.L., Aeronautica
Macchi S.P.A. Models AL60, AL60-B, AL60-F5, and AL60-C5,
Aeronautica Macchi & Aerfer Model AM-3, Aeronca Inc.
Models 15AC and S15AC, Aerospatiale Model TB20 Trinidad,
Arctic Aircraft Co., Inc. Models S-1A, S-1A-65F, S-1A-
85F, S-1A-90F, S-1B1 (Army L-67 XL-6), and S-1B2, Avions
Mudry et Cie Model CAP 10B, American Champion Models
(Bellanca, Aeronca) 7AC, 7ACA, S7AC (L-16A), 7BCM (L-
16B), 7CCM, 7DC, S7DC, 7EC, S7EC, 7ECA, 7FC, 7GC, 7GCA,
7GCCA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KC, 7KCAB, 8KCAB,
8GCBC, 11AC, S11AC, 11BC, S11BC, 11CC, and S11CC,
Bellanca Aircraft Corporation, Models 14-9, 14-9L, 14-12F-
3, 14-13, 14-13-2, 14-13-3, 14-13-3W, 14-19, 14-19-2, 14-
19-3A, 17-30, 17-31, 17-31TC, 17-30A, 17-31A, and 17-
31ATC, Biemond, C. Model Teal CB1, Board, G.R. Models
Columbia XJL-1 and Bolkow Jr., Clark Aircraft, Inc.
Models 12 and 1000, Falcon Aircraft Corporation Model F-
1, Flug und Fahrzeugwerke AG Model AS 202/15 ``Brand,''
Found Brothers Model FBA-2C, Fuji Heavy Industries Models
FA-200-160, FA-200-180, and FA-200-180AO, Funk Aircraft
Model Funk C, Kearns, Edward Scott (Garcia, Henry S.)
Model (Emigh) Trojan A-2, Swift Museum Foundation, Inc.
Model (Globe) GC-1A, GC-1B, Goodyear Aircraft Model GA-
22A, Great Lakes Aircraft Model 2T-1A-1 and 2T-1A-2,
Grumman American Models G-164, G-164A, G-164B, AA-1, AA-
1A, AA-1B, AA-1C, AA-5, AA-5A, and AA-5B, Commander
Aircraft (Gulfstream) Models 112, (112A, 112B, 112TC,
112TCA, 114, and 114A, Helio Enterprises Models H-250, H-
295 (USAF U-10D), H-391 (USAF YL-24), H-395 (SAF L-28A),
H-395A, HT-295, and H-700, Prop-Jets, Inc. (Interceptor
Corp., Aero Commander, Meyers) Models 200, 200A, 200B,
200C, and 200D, C. Itoh Aircraft Maintenance &
Engineering Co. LTD. Model N-62, Jamieson Corporation
Model J-2-L1B, Jodel, Avion Models D-140-B, DR-1050, D-
1190, and 150, Lake Models C-1, C-2-IV, LA-4, LA-4-200,
and LA-4-250, Luscombe Aircraft Corp. Models 8, 8A, 8B,
8C, 8D, 8E, 8F, T-8F, and 11A, Maule Aerospace Technology
Corp. Models Bee Dee M-4, M-4, M-4C, M-4S, M-4T, M-4-
180C, M-4-180S, M-4-210, M-4-201C, M-4-210S, M-4-210T, M-
4-220S, M-4-220T, M-5-180C, M-5-200, M-5-210C, M-5-210TC,
M-T-220C, M-5-235, M-5-235C, M-6-180, M-6-235, M-7-235,
MX-7-180, MX-7-235, Messerschmitt-Bolkow Models BO-209-
150 FV&RV, BO209-160 FV&RV, BO-209, and 150OFF, Nardi
S.A. Model FN-333, Jimmie Thompson Enterprise (Navion
Rangemaster Aircraft Corporation) Models Navion (L-17A),
Navion A (L-17B, L-17C), Navion B, D, E, F, G, and H,
White International Ltd. Models (Pitts) S-1S, S-1T, S-2,
and S-2A, Procaer S.P.A. Models F 15/B, F 15/C, and F 15/
E, Gulfstream Aerospace Corporation (Rockwell) Models
111, 112, 112B, 112TC, 112TCA, and 114, Aermacchi S.p.A
Models S.205, S.205-18F, S.205-18/R, S.205-20/F, S.205-20/
R, S.205-22/R, S.208, S.208A, F.260, and F.260B, Socata--
Groupe Aerospatiale Models Rallye Series MS880B, MS885,
MS892-A-150, MS892E-150, MS893A, MS893E, MS894A, MS894E,
TB9, TB10, and TB21, Stinson Models 108-2 and108-3, Sud
Aviation Models Gardan GY.80-1500, GY.80-160, and GY.80-
180, Taylorcraft Aircraft Company Models F19, F21, and
F21A, Univair Aircraft Corporation (Forney) Models F-1, F-
1A, (ERCO) E, 415D, (ALON) A-2, A20a, (Mooney) M10,
(Mooney) (ERCO) 415-C, and 415-CD, Augustair, Inc. (Varga
Aircraft Corporation) Models 2150, 2150A, and 2180.
----------------------------------------------------------------------------------------------------------------
Note 1: The above list includes the aircraft where the Precise
Flight, Inc. Model SVS III standby vacuum systems could be installed
through STC. This list is not meant to be exhaustive nor does it
include all aircraft with the systems installed through field
approval.
Note 2: This AD applies to any aircraft with a standby vacuum
system installed that is identified in the preceding applicability
provision, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For
aircraft that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if the unsafe condition has not been eliminated, the request
should include specific proposed actions to address it.
Compliance: Required as indicated in the body of this AD, unless
already accomplished. To detect and correct problems with the
standby vacuum system before failure or malfunction and to provide
operating procedures for the pilot regarding the use and limitations
of this system, accomplish the following:
(a) Within the next 30 calendar days after the effective date of
this AD, accomplish whichever (paragraph (a)(1) or (a)(2) below) of
the following that applies:
(1) For airplanes with the affected standby vacuum system
installed in accordance with the applicable STC, incorporate the
applicable Precise Flight, Inc. Airplane Flight Manual Supplement
(AFMS) for Standby Vacuum Systems (each document corresponds with
the applicable STC as presented in the chart below) into the
Airplane Flight Manual (AFM), including installing all placards
specified in these AFMS's; or insert a copy of the Appendix to this
AD into the AFM, including installing all placards specified in the
Appendix:
------------------------------------------------------------------------
Applicable STC AFMS date
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SA2160NM.................................. May 7, 1998.
SA2161NM.................................. August 6, 1998.
SA2162NM.................................. August 6, 1998.
SA2163NM.................................. August 6, 1998.
SA2164NM.................................. August 6, 1998.
SA2166M................................... August 6, 1998.
SA2167NM.................................. August 6, 1998.
SA2168NM.................................. August 6, 1998.
SA2683NM.................................. August 6, 1998; or
------------------------------------------------------------------------
(2) For airplanes with the affected standby vacuum system
installed through field approval, insert the Appendix to this AD
into the AFM, including installing all placards specified in the
Appendix.
(b) Within the next 12 calendar months after the effective date
of this AD, and thereafter at intervals specified in the following
paragraphs, inspect the push-pull cable, vacuum lines, saddle
fittings, and shuttle valve for correct installation and damage
(wear, chafing, deterioration, etc.). Accomplish these inspections
in accordance with Precise Flight Instructions for Continued
Airworthiness (Section 3.3 of Installation Report No. 50050),
Revision 25, dated August 26, 1996.
(1) Reinspect the push-pull cable, vacuum lines, and saddle
fittings at intervals not to exceed 12 calendar months; and
(2) Reinspect the shuttle valve at intervals not to exceed 24
calendar months.
(c) Prior to further flight after each inspection required by
paragraph (b) of this AD, accomplish the following in accordance
with Precise Flight Instructions for Continued Airworthiness
(Section 3.3 of Installation Report No. 50050), Revision 25, dated
August 26, 1996.
(1) Correct any discrepancy found; and
(2) Conduct a function test of the vacuum system and assure
proper function.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue, SW, Renton,
[[Page 66751]]
Washington 98055-4065. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Seattle ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(f) The inspections, corrections, and test required by this AD
shall be done in accordance with Precise Flight Instructions for
Continued Airworthiness (Section 3.3 of Installation Report No.
50050), Revision 25, dated August 26, 1996. This incorporation by
reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Precise Flight, Inc., 63120 Powell Butte Road, Bend,
Oregon 97701. Copies may be inspected at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106, or at the Office of the Federal Register, 800 North
Capitol Street, NW, suite 700, Washington, DC.
(g) This amendment becomes effective on January 14, 2000.
Appendix to Docket No. 98-CE-87-AD--Precise Flight, Inc. AFMS for
Standby Vacuum System
System Description
A Precise Flight Standby Vacuum System may be installed to
provide a temporary vacuum system in the event of a primary vacuum
failure. The Standby Vacuum System operates on the differential
between the intake manifold and ambient air pressure and is directed
through a shuttle valve system to drive your flight instruments.
I. Operating Limitations
A. Instructions
1. The Standby Vacuum System is for emergency or standby use
only and not for dispatch purposes.
2. Vacuum powered and/or Vacuum gyro directed autopilot
operation may be unreliable when the Standby Vacuum System is the
sole source of vacuum. Vacuum powered or vacuum gyro directed
autopilot should be OFF when operating with a failed primary vacuum
system.
3. The Supplemental Vacuum System is not designed to operate
pneumatic de-ice systems. DO NOT operate a pneumatic de-ice system
when operating with a failed primary vacuum system.
4. Above 10,000 ft. pressure altitude, engine power settings may
have to be significantly reduced to provide adequate vacuum power
for proper gyro instrument operation.
5. The following placards are required to be in full view of
pilot:
B. Placards
Placard to be located on the push/pull control cable.
Placard to be located around the LED for the pump inop warning
light.
Placard to be placed in front and in full view of the pilot.
------------------------------------------------------------------------
-------------------------------------------------------------------------
STANDBY VACUUM SYSTEM EQUIPPED: FOR OPERATING INSTRUCTIONS AND
LIMITATIONS SEE SUPPLEMENT IN OWNERS MANUAL OR PILOTS OPERATING
HANDBOOK
------------------------------------------------------------------------
One of the following placards must be placed in full view of the
pilot near the instrument vacuum indicator after appropriate entries
have been made.
Approximate Standby Vacuum Available--Altitude--Power Chart for Aircraft With Constant Speed Propeller--Maximum
Continuous RPM
----------------------------------------------------------------------------------------------------------------
Press alt. (ft.) RPM Man. pressure SVS Vacuum in. hg min.
----------------------------------------------------------------------------------------------------------------
2000................................. Max. Cont..............
4000................................. Max. Cont..............
6000................................. Max. Cont..............
8000................................. Max. Cont..............
10,000............................... Max. Cont..............
----------------------------------------------------------------------------------------------------------------
Approximate Standby Vacuum Available--Altitude--Power Chart for Aircraft
With a Fixed Pitch Propeller
------------------------------------------------------------------------
SVS Vacuum in. hg
Press alt. (ft.) RPM min.
------------------------------------------------------------------------
2000........................
4000........................
6000........................
8000........................
10,000......................
------------------------------------------------------------------------
II. Operating Procedures
A. Normal Procedures
1. Ground Check
a. Cycle the Standby Vacuum Control Knob OUT--ON--and return
Control Knob IN--OFF--position.
2. Before Takeoff
a. Idle Engine at low speed, momentarily pull the standby vacuum
knob out--ON--and check vacuum gauge. Normally, the vacuum reading
will be slightly higher. After checking system push Standby Vacuum
System knob IN--OFF--. Check that vacuum gauge has returned to the
previous reading.
3. Enroute
a. Regularly check vacuum gauge and monitor warning light for
proper vacuum system operation.
B. Emergency Procedures
1. Primary Vacuum Failure Warning Light Illuminates
a. Pull the Standby Vacuum System knob OUT--ON--and adjust
throttle setting as required to maintain adequate vacuum for the
primary instruments--Suction Gauge Reading in the Green Arc--If
necessary descend to a lower altitude to obtain a larger
differential between manifold and ambient pressure. Vacuum power
must be closely monitored by checking the vacuum gauge frequently.
b. The SVS is not designed for continued IFR flight. Immediate
steps should be taken to return to VFR conditions or to land. If
this is not possible, IFR flight should be continued only as long as
necessary to return to VFR conditions or land the airplane.
WARNING: FAILURE OF THE VACUUM SYSTEM STILL CONSTITUTES AN
EMERGENCY SITUATION REGARDLESS OF THE INSTALLATION OF THE SVS. IT
MAY NOT BE POSSIBLE TO MAINTAIN A SAFE ALTITUDE AND MAKE USE OF THE
SVS. IN SUCH A SITUATION THE AIRPLANE MUST BE FLOWN USING NON-VACUUM
POWERED INSTRUMENTS.
c. If descent is impractical:
Periodically and temporarily reduce power as required
to provide adequate vacuum to the aircraft primary instruments.
Reapply power as required, while comparing vacuum
driven gyros against the Turn and Bank Indicator, Turn Coordinator,
VSI and/or other flight instruments.
When an obvious discrepancy is noted between the vacuum
driven instruments and other flight instrumentation. Periodically
and temporarily reduce power as required to provide adequate vacuum
to the aircraft primary instruments.
III. Performance
No Change.
[[Page 66752]]
Issued in Kansas City, Missouri, on November 15, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-30519 Filed 11-29-99; 8:45 am]
BILLING CODE 4910-13-U
