[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