[Federal Register Volume 61, Number 156 (Monday, August 12, 1996)]
[Rules and Regulations]
[Pages 41733-41735]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-20307]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-157-AD; Amendment 39-9708; AD 96-16-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727-100 and -200 Series
Airplanes With a Main Deck Cargo Door Installed in Accordance With
Supplemental Type Certificate (STC) SA1797SO
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 727-100 and -200 series
airplanes. This action requires an inspection to detect discrepancies
of internal wires and electrical components of the control box of the
main deck cargo door; modification of the wiring and components of the
control box of the main deck cargo door; and a revision of the Airplane
Flight Manual to impose an operational limitation of the motor pump
power relay and pump motor. This amendment is prompted by results of an
engineering review of the wiring diagram of the main deck cargo door
installations, which revealed potential failures of the control box and
hydraulic pump assembly installed in accordance with the STC. The
actions specified in this AD are intended to prevent such failures,
which could result in an inadvertent opening of the main deck cargo
door during flight, with resultant major structural damage and possible
reduced controllability of the airplane.
DATES: Effective August 27, 1996.
-The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 27, 1996.
-Comments for inclusion in the Rules Docket must be received on or
before October 11, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-157-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
-The Boeing Manufacturing Drawing D65446 referenced in this AD may
be obtained from Boeing Commercial Airplane Group, P.O. Box 3707,
Seattle, Washington 98124-2207. FAA Advisory Circular (AC) 4313-1A,
referenced in this AD, may be obtained from the Superintendent of
Documents, U.S. Government Printing Office, Washington, DC 20402. Both
of these documents may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
Atlanta Aircraft Certification Office, Small Airplane Directorate,
Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park,
Georgia 30337-2748; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Randy Avera, Systems Engineer, ACE-
116A, FAA, Atlanta Aircraft Certification Office, Small Airplane
Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160,
College Park, Georgia 30337-2748; telephone (404) 305-7381; fax (404)
305-7348.
SUPPLEMENTARY INFORMATION: The FAA recently conducted an engineering
review of the wiring diagram of the main deck cargo door installations
on Boeing Model 727-100 and -200 series airplanes that have been
modified in accordance with Supplemental Type Certificate (STC)
SA1797SO. The results of this review revealed the existence of two
unsafe conditions related to the control box and hydraulic pump
assembly installed on these airplanes:
-1. Due to the close proximity to the relays, a 28-volt wire could
become chafed as a result of vibration and, consequently, could short
to power a single DC relay (AN 3311-2). This short to power could
energize the DC relay and simultaneously apply electrical power to the
hydraulic pump motor and to the control valve of the main deck cargo
door.
-2. Failure of an electrical relay on the 115-volt AC power circuit
could cause the hydraulic pump motor to become energized and,
consequently, produce full hydraulic pressure in the pump. Such
available pressure could unlock the main deck cargo door.
-These conditions, if not corrected, could result in an inadvertent
opening of the main deck cargo door during flight, which could result
in major structural damage and possible reduced controllability of the
airplane.
Explanation of Relevant Service Information
-The FAA has issued Advisory Circular (AC) 43.13-1A, Change 3,
dated 1988, which contains the following sections of Chapter 11
(``Electrical Systems''):
-1. Section 1 (``Care of Electrical Systems''),
-2. Section 3 (``Electrical Wire''),
-3. Section 5 (``Connectors''), and
-4. Section 7 (``Routing, Tying, Lacing, and Clamping'').
-The FAA also has reviewed and approved Chapter 20, ``Standard
Wiring Practices'', of Boeing Wiring Diagram Manual Document D6-54446,
Revision 21, dated June 1, 1994.
-These documents describe procedures for verifying that the wire
and wire bundles are properly installed and restrained, and for
reinstalling and restraining any wire or component that has been
altered.
Explanation of the Requirements of the Rule
-Since an unsafe condition has been identified that is likely to
exist or develop on other Boeing Model 727-100 and -200 series
airplanes of the same type design, equipped with a main deck cargo door
installed in accordance with STC SA1797SO, this AD is being issued to
prevent an inadvertent opening of the main deck cargo door during
flight, which can result in major structural damage and possible
reduced controllability of the airplane. This AD requires the following
actions:
-1. Performing a one-time visual inspection of the internal wires
and electrical components of the control box of the main deck cargo
door to detect discrepancies, and repair, if necessary.
[[Page 41734]]
(These discrepancies include chafed, crimped, crushed, or damaged
electrical wires or wire bundles inside the control box of the cargo
door; loose electrical wire connections; abnormally pulled or twisted
individual wires or wire bundles; any removal of insulation from the
conductor in the control box; and any damaged protective grommets.)
-2. Verifying that the wire and wire bundles are properly installed
and restrained; and reinstalling and restraining any wire or component
that has been altered.
-3. Submitting a report of the inspection results (both positive
and negative findings) to the FAA.
-4. Revising the Limitations Section of the FAA-approved Airplane
Flight Manual (AFM) to impose an operational limitation of the motor
pump power relay and pump motor. This limitation requires the flight
crew to verify that certain circuit breakers supplying electrical power
to the hydraulic pump motor are pulled prior to taxi. It also requires
that, prior to each taxi and takeoff after closing the cargo door,
these circuit breakers are set to the open condition, tagged, and
secured for flight.
-5. Modifying the wiring and components of the control box of the
main deck cargo door to preclude the identified problems. Aeronautical
Engineers, Inc. (AEI), which is the holder of the subject STC,
currently is developing a change to the wiring diagram that will
address this.
Certain of the actions are required to be accomplished in
accordance with the documents described previously. Certain other
actions are required to be accomplished in accordance with a method
approved by the FAA.
Determination of Rule's Effective Date
-Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
-Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
-Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
-Commenters wishing the FAA to acknowledge receipt of their
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket Number 96-NM-157-AD.'' The postcard will be date
stamped and returned to the commenter.
Regulatory Impact
-The regulations adopted herein will 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
-The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from 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:
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 the following new
airworthiness directive:
96-16-08 BOEING: Amendment 39-9708. Docket 96-NM-157-AD.
Applicability: Model 727-100 and -200 series airplanes that have
been modified in accordance with Supplemental Type Certificate (STC)
SA1797SO, certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes 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 (d) 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, unless accomplished
previously.
-To prevent the inadvertent opening of the main deck cargo door
during flight, which could result in major structural damage and
possible reduced controllability of the airplane, accomplish the
following:
-(a) Accomplish the actions specified in paragraphs (a)(1),
(a)(2), (a)(3), and (a)(4) of this AD at the time specified in each
of those paragraphs:
-(1) Within 3 days after the effective date of this AD, perform
a visual inspection of internal wires and electrical components of
the control box of the main deck cargo door to detect the following
discrepancies:
-(i) chafed, crimped, crushed, or damaged electrical wires or
wire bundles inside the control box of the cargo door;
-(ii) loose electrical wire connections;
-(iii) abnormally pulled or twisted individual wires or wire
bundles;
-(iv) any removal of insulation from the conductor in the
control box; or
-(v) any damaged protective grommets.
[[Page 41735]]
(2) If any discrepancy is detected during the inspection
required by paragraph (a)(1) of this AD, prior to further flight,
repair it in accordance with a method approved by the Manager, FAA,
Atlanta Aircraft Certification Office (ACO), Small Airplane
Directorate.
(3) Following accomplishment of paragraphs (a)(1) and, if
applicable, (a)(2) of this AD, verify that the wire and wire bundles
are properly installed and restrained, and reinstall and restrain
any wire or component that has been altered, in accordance with the
document identified in either paragraph (a)(3)(i) or (a)(3)(ii) of
this AD.
(i) Section 1 (``Care of Electrical System''); Section 3
(``Electric Wire''); Section 5 (``Connectors''); and Section 7
(``Routing, Tying, Lacing, and Clamping); of Chapter 11
(``Electrical Systems'') of FAA Advisory Circular AC 4313-1A, Change
3, dated 1988; or
(ii) Chapter 20 (``Standard Wiring Practices'') of Boeing Wiring
Diagram Manual Document D6-54446, Revision 21, dated June 1, 1994.
(4) Within 10 days after accomplishing the inspection required
by paragraph (a)(1) of this AD, submit a report of the inspection
results (both positive and negative findings) to the Manager, FAA,
Atlanta Aircraft Certification Office, Small Airplane Directorate,
Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park,
Georgia 30337-2748; telephone (404) 305-7381; fax (404) 305-7348.
Information collection requirements contained in this regulation
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
(b) Within 3 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following statement. This may be accomplished
by inserting a copy of this AD in the AFM.
``Operational Restriction
Prior to taxi, verify that the alternating current (AC) or
direct current (DC) circuit breakers that supply electrical power to
the hydraulic pump motor are PULLED to interrupt power to the motor
pump power relay and pump motor.
Note 1: The 28VDC circuit breaker is located in the electrical
equipment compartment on the J9 battery shield panel next to the
auxiliary power unit (APU) starter circuit breaker. The 115VAC
circuit breakers are located on the P6 breaker panel to the right of
the Flight Engineers station. These circuit breakers are identified
as ``Cargo Door Hydraulic Pump''.
Prior to each taxi and take-off after closing the cargo door,
set these circuit breakers to an open condition. Tag and secure the
circuit breakers for flight.
After landing and taxiing to the ramp, the circuit breakers may
be RESET to facilitate cargo door opening.''
(c) Within 90 days after the effective date of this AD, modify
the wiring and components of the control box of the main deck cargo
door, in accordance with a method approved by the Manager, FAA,
Atlanta Aircraft Certification Office (ACO), Small Airplane
Directorate.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, FAA, Atlanta Aircraft Certification
Office (ACO), Small Airplane Directorate. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Atlanta ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(e) Special flight permits may be issued in accordance with
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.
(f) Certain actions shall be done either in accordance with
Sections 1, 3, 5, and 7 of Chapter 11 (``Electrical Systems'') of
FAA Advisory Circular (AC) 4313-1A, Change 3, dated 1988; or in
accordance with Chapter 20 (``Standard Wiring Practices'') of Boeing
Wiring Diagram Manual Document D6-54446, Revision 21, dated June 1,
1994. Sections 1, 3, 5, and 7 of Chapter 11 of FAA Advisory Circular
AC 4313-1A contain the following list of effective pages:
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Date shown on
Section referenced- Page number- Change level shown on page- page
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Section 1, ``Care of Electrical 173-174-................ Original-.................... 1972
Systems''.
Section 3, ``Electric ``Wire''---..... 179, 180, 180-1,180-2, 3............................ 1988
181, 181-1, 181-2, 182,
182-1, 182-2, 183-185,
185-1, 185-2, 186, 188,
188-1, 188-2.
187, 189-193-........... Original-.................... 1972
Section 5, ``Connectors''-............ 196,200-................ 3-........................... 1988
197-199................. Original..................... 1972
Section 7, ``Routing,Tying, Lacing, 203, 204, 206-209-...... Original..................... 1972
and Clamping''-.
- 205, 205-1, 205-2....... 3-........................... 1988
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-Chapter 20 of Boeing Wiring Diagram Manual Document D6-54446
contains the following list of effective pages:
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Page title and number Date shown on page
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Title Page-.......................... December 1, 1991.
Revision Transmittal Pages 1-6....... June 1, 1994.
Revision Record Pages 1, 2-.......... December 1, 1991.
Temporary Revision Record Pages 1, 2 - December 1, 1991.
.
List of Effective Pages 1-30......... June 1, 1994.
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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 of Boeing Manufacturing Drawing D65446 may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707,
Seattle, Washington 98124-2207. Copies of FAA Advisory Circular (AC)
4313-1A may be obtained from Superintendent of Documents, U.S.
Government Printing Office, Washington, DC 20402. Copies of all of
these documents may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA,
Atlanta Aircraft Certification Office, Small Airplane Directorate,
Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park,
Georgia 30337-2748; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on August 27, 1996.
Issued in Renton, Washington, on August 2, 1996.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-20307 Filed 8-9-96; 8:45 am]
BILLING CODE 4910-13-U
