[Federal Register Volume 60, Number 178 (Thursday, September 14, 1995)]
[Rules and Regulations]
[Pages 47687-47689]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22646]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-58-AD; Amendment 39-9369; AD 95-19-07]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
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
applies to Fairchild Aircraft SA226 and SA227 series airplanes equipped
with certain main landing gear (MLG) and nose landing gear (NLG). This
action requires repetitively inspecting, using ultrasonic methods, the
left-hand and right-hand MLG yokes and the NLG yokes for stress
corrosion cracking, and, if any cracked yokes are found that exceed
certain limits, either replacing the cracked yoke, the yoke/cylinder
combination, or the affected MLG or NLG assembly. Several reports of
landing gear failures on the affected airplanes that have the affected
MLG or NLG yokes installed prompted this action. The actions specified
by this AD are intended to prevent MLG or NLG failure caused by stress
corrosion cracks in the yokes, which, if not detected and corrected,
could result in loss of control of the airplane during landing
operations.
DATES: Effective September 28, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 28, 1995.
Comments for inclusion in the Rules Docket must be received on or
before November 4, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-CE-58-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490;
telephone (210) 824-9421. This information may also be examined at the
FAA, Central Region, Office of the Assistant Chief Counsel, Attention:
Rules Docket 95-CE-58-AD, Room 1558, 601 E. 12th Street, 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: Mr. Werner Koch, Aerospace Engineer,
FAA, Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150; telephone (817) 222-5133; facsimile (817) 222-5960.
SUPPLEMENTARY INFORMATION: The FAA has received several reports of main
landing gear (MLG) and nose landing gear (NLG) failure on Fairchild
Aircraft SA226 and SA227 series airplanes. The airplanes in these
incidents are equipped with part number (P/N) OAS5453 MLG and P/N
OAS5451 NLG.
Metallurgical analysis of the yokes of the right-hand and left-hand
MLG and NLG gear on several of these airplanes revealed that the
failure was initiated by stress corrosion cracking of the yokes, which
started as corrosion fatigue. This condition, if not detected and
corrected, could result in loss of control of the airplane during
landing operations.
Fairchild Aircraft has issued Service Bulletin (SB) 226-32-065, SB
227-32-039, and SB CC7-32-007, all Issued: August 16, 1995, which
specify procedures for ultrasonically inspecting the left-hand and
right-hand MLG yoke, P/N 5453005-1, 5453005-3, or 5453005-5, and the
NLG yoke, P/N 5451005-1, on Fairchild Aircraft SA226 and SA227 series
airplanes.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent MLG or NLG failure
caused by stress corrosion cracks of the yokes, which, if not detected
and corrected, could result in loss of control of the airplane during
landing operations.
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Aircraft SA226 and SA227 series
airplanes of the same type design, this AD requires repetitively
inspecting, using ultrasonic methods, the left-hand and right-hand MLG
yokes and the NLG yokes for stress corrosion cracking, and, if any
cracked yokes are found that exceed certain limits, either replacing
the cracked yoke, the yoke/cylinder combination, or the affected MLG or
NLG assembly. Accomplishment of the ultrasonic inspections shall be in
accordance with either Fairchild Aircraft SB 226-32-065, SB 227-32-039,
and SB CC7-32-007, all Issued: August 16, 1995, as applicable. The
replacement, if necessary, shall be accomplished in accordance with the
applicable maintenance manual.
Since a situation exists (possible loss of control of the airplane
during landing operations) that requires the immediate adoption of this
regulation, it is found that notice and opportunity for public prior
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 immediate flight safety and, thus, was not
preceded by notice and opportunity to 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 should identify the
[[Page 47688]]
Rules Docket number and be submitted in triplicate to the address
specified above. 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 request must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 95-CE-58-AD.'' The postcard will be date stamped and
returned to the commenter.
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 and that must be issued immediately to correct an unsafe
condition in aircraft, and 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 (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
95-19-07 Fairchild Aircraft: Amendment 39-9369; Docket No. 95-CE-
58-AD.
Applicability: Models SA226-T, SA226-AT, SA226-TC, SA226-T(B),
SA227-AC, SA227-AT, SA227-BC, SA227-TT, SA227-CC, and SA227-DC
airplanes (all serial numbers), certificated in any category, that
are equipped with one or more of the following:
1. Main landing gear part number (P/N) OAS5453-*(dash numbers 1
through 19) with either a P/N 5453005-1, 5453005-3, or 5453005-5
yoke installed; or
2. Nose landing gear P/N OAS5451-*(dash numbers 1 through 17)
with a P/N 5451005-1 yoke installed.
Note 1: This AD applies to each airplane identified in the
preceding applicability revision, regardless of whether it has been
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 (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 initially as follows and thereafter as
indicated in the body of this AD:
1. Within the next 75 hours time-in-service (TIS) after the
effective date of this AD, unless already accomplished; and
2. Upon the installation of one of the affected main landing
gear or nose landing gear assemblies or yokes.
To prevent main landing gear or nose landing gear failure caused
by stress corrosion cracks of the yoke, which, if not detected and
corrected, could result in loss of control of the airplane during
landing operations, accomplish the following:
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
(a) Inspect, using ultrasonic methods, the left-hand and right-
hand main landing gear and the nose landing gear yoke for stress
corrosion cracking in accordance with one of the following, as
applicable:
(1) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Service
Bulletin (SB) 226-32-065, Issued: August 16, 1995.
(2) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 227-
32-039, Issued: August 16, 1995.
(3) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB CC7-
32-007, Issued: August 16, 1995.
(b) Reinspect or replace the right-hand or left-hand main
landing gear or nose landing gear yoke as follows based on the
results of any required inspection:
(1) If no cracks are found or a crack is found that is less than
.25 inch, accomplish the following:
(i) Prior to further flight after the inspection required by
paragraph (a) of this AD, clean the main landing gears and nose
landing gear yoke and piston in accordance with Figure 2 of the
service bulletins referenced in paragraphs (a)(1), (a)(2), and
(a)(3) of this AD;
(ii) Prior to further flight after the inspection required by
paragraph (a) of this AD, apply a small bead of Products Research
and Chemical Corporation PR-1422 or PR-1435 sealant to the main
landing gears and nose landing gear yoke as shown in Figure 2 of the
service bulletins referenced in paragraphs (a)(1), (a)(2), and
(a)(3) of this AD, and as described in the SA226/227 Series Service
Repair Manual, Chapter 51-30-03, Standard Practices--Sealing; and
(iii) Reinspect at intervals not to exceed 2,000 hours TIS
provided no cracks are found that are .25 inch or more in length.
(2) If a crack is found with a length of .25 inch or more but
not more than .50 inch, reinspect at intervals not to exceed 1,000
hours TIS provided the crack is no longer than .50 inch.
(3) If a crack is found with a length more than .50 inch but not
more than .75 inch, reinspect at intervals not to exceed 500 hours
TIS provided the crack is no longer than .75 inch.
(4) If a crack is found with a length more than .75 inch but not
more than 1 inch, reinspect at intervals not to exceed 200 hours TIS
provided the crack is no longer than 1 inch.
(5) If a crack is found with a length more than 1 inch but not
more than 1.5 inches, accomplish the following:
(i) Within 100 hours TIS after the inspection required by
paragraph (a) of this AD, replace the cracked part with a new part
in accordance with the applicable maintenance manual. This may be
accomplished by replacing the cracked yoke, the total gear assembly,
or the yoke/cylinder combination;
[[Page 47689]]
(ii) Prior to further flight after replacing the cracked part,
clean the main landing gears and nose landing gear yoke and piston
in accordance with figure 2 of the service bulletins referenced in
paragraphs (a)(1), (a)(2), and (a)(3) of this AD;
(iii) Prior to further flight after replacing the cracked part,
apply a small bead of Products Research and Chemical Corporation PR-
1422 or PR-1435 sealant to the main landing gears and nose landing
gear yoke as shown in Figure 2 of the service bulletins referenced
in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and as
described in the SA226/227 Series Service Repair Manual, Chapter 51-
30-03, Standard Practices--Sealing; and
(iv) Repeat the inspections specified in paragraphs (a) and (b)
of this AD and replace the part as required.
(6) If a crack is found with a length more than 1.5 inches,
accomplish the following:
(i) Prior to further flight after the inspection required by
paragraph (a) of this AD, replace the cracked part with a new part
in accordance with the applicable maintenance manual. This may be
accomplished by replacing the cracked yoke, the total gear assembly,
or the yoke/cylinder combination;
(ii) Prior to further flight after replacing the cracked part,
clean the main landing gears and nose landing gear yoke and piston
in accordance with figure 2 of the service bulletins referenced in
paragraphs (a)(1), (a)(2), and (a)(3) of this AD;
(iii) Prior to further flight after replacing the cracked part,
apply a small bead of Products Research and Chemical Corporation PR-
1422 or PR-1435 sealant to the main landing gears and nose landing
gear yoke as shown in Figure 2 of the service bulletins referenced
in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and as
described in the SA226/227 Series Service Repair Manual, Chapter 51-
30-03, Standard Practices--Sealing; and
(iv) Repeat the inspections specified in paragraphs (a) and (b)
of this AD and replace the part as required.
(7) If multiple cracks are found, add the total length of the
cracks and use the criteria presented in paragraphs (b)(1) through
(b)(6) of this AD, including all subparagraph designations, to
establish repetitive inspection intervals or replacement times.
(c) The MLG and NLG yokes affected by this AD are manufactured
by Ozone Industries, Inc. Replacing these yokes with approved parts
manufactured by Fairchild Aircraft eliminates the repetitive
inspection requirements of this AD.
(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
compliance time that provides an equivalent level of safety may be
approved by the Manager, Airplane Certification Office (ACO), FAA,
2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. The request
shall be forwarded through an appropriate FAA Maintenance Inspector,
who may add comments and then send it to the Manager, Fort Worth
ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) The inspections required by this AD shall be done in
accordance with Fairchild Aircraft Service Bulletin 226-32-065,
Issued: August 16, 1995, Fairchild Aircraft Service Bulletin 227-32-
039, Issued: August 16, 1995, or Fairchild Aircraft Service Bulletin
CC7-32-007, Issued: August 16, 1995, as applicable. 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 Fairchild Aircraft, P.O. Box 790490,
San Antonio, Texas 78279-0490. Copies may be inspected at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri, or at the Office of the
Federal Register, 800 North Capitol Street NW., 7th Floor, suite
700, Washington, DC.
(g) This amendment (39-9369) becomes effective on September 28,
1995.
Issued in Kansas City, Missouri, on September 6, 1995.
Gerald W. Pierce,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-22646 Filed 9-13-95; 8:45 am]
BILLING CODE 4910-13-U
