[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13491-13493]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6767]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-68-AD; Amendment 39-10403; AD 98-06-25]
RIN 2120-AA64


Airworthiness Directives; Fairchild Aircraft Inc. Models SA226-
AT, SA226-TC, SA227-AC, and SA227-AT Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Fairchild Aircraft Inc. (Fairchild) Models SA226-AT, SA226-
TC, SA227-AC, and SA227-AT airplanes. This action would require 
inspecting the cargo door lower belt frames at the cargo latch 
receptacles for cracks in the belt frames, repairing any cracks, and 
reinforcing the cargo door lower belt frames by installing doublers. 
The AD is the result of a decompression incident during flight caused 
by fatigue at the bottom of the cargo door on a Fairchild Model SA226-
TC. The actions specified by this AD are intended to prevent the 
failure of the cargo door in flight, which could cause decompression 
injuries to passengers and substantial structural damage to the 
airplane.

DATES: Effective April 27, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 27, 1998.

ADDRESSES: Service information that applies to this AD may be obtained 
from Fairchild Aircraft Inc., P. O. Box 790490, San Antonio, Texas 
78279-0490, telephone (210) 824-9421. This information may also be 
examined at the Federal Aviation Administration (FAA), Central Region, 
Office of the Regional Counsel, Attention: Rules Docket 96-CE-68-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. Hung Viet Nguyen, Aerospace 
Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham 
Boulevard, Fort Worth, Texas 76193-0150; telephone (817) 222-5155; 
facsimile (817) 222-5960.

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 Fairchild Models 
SA226-AT, SA226-TC, SA227-AC, and SA227-AT airplanes was published in 
the Federal Register on June 4, 1997 (62 FR 30483). The action proposed 
would require inspecting the lower belt frames at the cargo latch 
receptacles for cracks. If cracks are found, the proposed AD would 
require repairing the cracks, prior to further flight, using a repair 
scheme provided by the manufacturer through the Ft. Worth Airplane 
Certification Office. If no cracks are found, the proposed action would 
require reinforcing the cargo door lower belt frames by installing 
doublers.

Since Issuance of the Proposed AD

    The proposed action required that if cracks were found, the owner/
operator should contact the FAA for an approved repair scheme from 
Fairchild Aircraft Inc. Since the Notice of Proposed Rulemaking was 
published, Fairchild has developed an FAA-approved repair scheme for 
the cargo door belt frames. This repair scheme eliminates the need to 
contact the Ft. Worth Airplane Certification Office, which makes it 
easier for the owner to fix the airplanes with cracks without waiting 
for an approved repair scheme to be developed for each individual 
request. In addition to the availability of a repair, the FAA has 
clarified the instructions for the inspection of the cargo door belt 
frames by referencing certain fuselage stations to be inspected for 
cracks. Accomplishment of these actions would be in accordance with the 
following service information:
     Fairchild Aircraft Corporation SA227 Series Service 
Bulletin No. 227-53-003, Issued: January 29, 1986, Revised: February 
13, 1986,
     Fairchild Aircraft Corporation SA226 Series Service 
Bulletin No. 226-53-007, Issued: May 7, 1981, Revised: February 17, 
1992,
     Fairchild Aircraft SA226/SA227 Structural Repair Manual 
(SRM), section 53-90-20, pages 2, 101, 102, 103, and 104; Initial 
Issue: March 1, 1983, Revision 24, dated August 27, 1997, or
     Fairchild Aircraft Approved Repair Procedure (ARP) 53-30-
9701, dated July 28, 1997.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the following comments.

[[Page 13492]]

Obtaining Repair Approval

    Several commenters express concern about access to a repair scheme 
and the ability of the FAA to provide a repair scheme outside normal 
business hours (8:00 a.m. to 4:30 p.m.). The commenters went on to say 
that in many cases, inspections and repairs are made overnight or on 
the weekends and waiting on the FAA to provide a repair scheme, on a 
case by case basis, could cause the commercial operators flight delays 
and cancellations. These commenters request that the FAA approve and 
make available a repair scheme prior to the effective date of the 
proposed AD. The FAA agrees and has approved a repair scheme developed 
by Fairchild Aircraft Inc. The final rule will be changed to reflect 
the name and number of these approved repair procedures.

Change of Compliance Time

    One commenter requested a change to the compliance times referenced 
in paragraphs (a) and (c) of the NPRM. The compliance time proposed was 
500 hours time-in-service (TIS) after the effective date of this AD for 
the initial inspection for cracks, and if no cracks were found within 
the next 500 hours TIS, installing a doubler to the cargo door belt 
frames. The commenter wants the initial inspection compliance time 
extended to 900 hours TIS after the effective date of this AD, to fit 
into the operators' scheduled maintenance to the cargo door belt 
frames. The FAA does not agree. The 500 hours TIS compliance time will 
assure that the affected airplanes are not flying with cracks in 
critical structure. Failure of the cargo door during flight would cause 
airplane decompression and possible injury to the passengers, as well 
as structural damage to the airplane. The 500 hours TIS initial 
inspection is imposed to assure that all the affected airplanes are 
checked for cracks in this area within a reasonable amount of time. The 
installation of the doubler to strengthen the cargo door belt frames is 
not required for another 500 hours TIS, in order to give the owners/
operator an opportunity to schedule this ``down-time'' into their 
flight schedules. If no cracks are found in the affected area, the 
owners/operators essentially have 1,000 hours total TIS to schedule the 
installation of the doublers. The final rule will not change as a 
result of this comment.

Crack Limits

    Two comments were received regarding the discussion in the NPRM 
preamble. The comments addressed the section directed to the 
differences between the manufacturer's service bulletin and the 
proposed action. The commenters said that the language in the preamble 
implied that the manufacturer's service bulletin allowed the operators 
to fly with cracks. Although it was not the intent of the FAA to 
suggest that the manufacturer allowed flying with cracks, the FAA 
agrees that the language in the preamble could be interpreted this way. 
The FAA was trying to point out that the compliance times in the 
service bulletin were different from those in the proposed action, and 
that the service bulletin referred the operator to the manufacturer for 
repairs, if cracks of one inch or larger were found. The service 
bulletin did not require the operator to contact the manufacturer for 
the repair scheme prior to further flight. This language is not 
repeated in the final rule, and since a repair scheme is now available 
directly from the manufacturer, the only difference between the 
manufacturer's service bulletin and the action required by this AD is 
the difference in compliance times. The compliance times required by 
this AD will take precedence over the compliance times in the Fairchild 
service bulletins. The final rule will reflect this change to the 
service and repair information in the body of the AD.

The FAA's Determination

    After careful review of all available information, including the 
service 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 changes and corrections 
will not change the meaning of the AD and will not add any additional 
burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 145 airplanes in the U.S. registry are 
affected by this AD, that it will take approximately 30 workhours per 
airplane to accomplish the initial inspection and installation of the 
reinforcing doubler, and that the average labor rate is approximately 
$60 an hour. Parts for the installation of the reinforcing doubler cost 
approximately $710 per airplane. Based on these figures, the total cost 
impact of this AD on U.S. operators is estimated to be $363,950 or 
$2,510 per airplane. The FAA has no way to determine the number of 
affected airplanes that may have already had this action accomplished.

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.
    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:

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:

98-06-25 Fairchild Aircraft Inc.: Amendment 39-10403; Docket No. 96-
CE-68-AD.

    Applicability: The following models and serial numbered 
airplanes, certificated in any category.

------------------------------------------------------------------------
              Models                           Serial numbers           
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SA226-AT..........................  AT001 through AT074.                
SA226-TC..........................  TC201 through TC419.                

[[Page 13493]]

                                                                        
SA227-AC..........................  AC406, AC415, AC416, AC420 through  
                                     AC456, AC458 through AC469, and    
                                     AC471 through AC478.               
SA227-AT..........................  AT423 through AT469.                
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    Note 1: This AD applies to each airplane 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 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 as indicated within the body of this AD, 
unless already accomplished.
    To prevent failure of the cargo door in flight, which, if not 
corrected, could cause decompression injuries to passengers and 
substantial structural damage to the airplane, accomplish the 
following:
    (a) Within the next 500 hours time-in-service (TIS) after the 
effective date of this AD, inspect the cargo door lower belt frames 
at the cargo latch receptacles for cracks in accordance with Part A 
of the ACCOMPLISHMENT INSTRUCTIONS section in Fairchild Aircraft 
SA226 Series Service Bulletin (SB) No. 226-53-007, Issued: May 7, 
1981; Revised: February 17, 1992, or Fairchild Aircraft SA227 Series 
SB No. 227-53-003, Issued: January 29, 1986; Revised: February 13, 
1986, whichever is applicable.
    (b) If cracks are found during the inspection required in 
paragraph (a) of this AD, prior to further flight, accomplish the 
following:
    (1) For belt frames located at Fuselage Station (F.S.) 438.060 
and F.S. 491.060, repair the belt frame by installing angle part 
number (P/N) 27-22206-009 or P/N 27-22206-010, in accordance with 
the Fairchild Aircraft SA226/227 Structural Repair Manual (SRM), 
Section 53-90-20, pages 2, 101, 102, 103, and 104; Initial Issue: 
March 1, 1983, Revision 24, dated August 27, 1997; or, Fairchild 
Aircraft Approved Repair Procedure (ARP) 53-30-9701, dated July 28, 
1997. The reinforcement doublers (P/N 27-22206-007 and -008) are 
also needed together with this repair.
    (2) For belt frames located at F.S. 454.501, F.S. 455.726, F.S. 
473.392, and F.S. 474.657, replace all four belt frames with new 
design frames, P/N 27-22207-008, 27-22208-005, 27-22208-005, and 27-
22207-007, respectively, in accordance with the Fairchild Aircraft 
SA226/227 SRM, Section 53-90-20, pages 2, 101, 102, 103, and 104; 
Initial Issue: March 1, 1983, Revision 24, dated August 27, 1997; 
or, Fairchild Aircraft ARP 53-30-9701, dated July 28, 1997. No 
reinforcement doublers are needed for these four new design belt 
frames.
    (c) If no cracks are found in all six belt frames during the 
inspection required by paragraph (a) of this AD, install 
reinforcement doublers in all six belt frames within 500 hours TIS 
from the initial inspection, in accordance with Part B of the 
ACCOMPLISHMENT INSTRUCTIONS of Fairchild Aircraft SA226 Series 
Service Bulletin (SB) No. 226-53-007, Issued: May 7, 1981; Revised: 
February 17, 1992, or Fairchild Aircraft SA227 Series SB No. 227-53-
003, Issued: January 29, 1986; Revised: February 13, 1986, whichever 
is applicable.
    (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 time that provides an equivalent 
level of safety may be approved by the Manager, Fort Worth Airplane 
Certification Office, 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 Airplane Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Manager, Fort Worth Airplane Certification Office.

    (f) The inspections and modifications required by this AD shall 
be done in accordance with the following service information:
     Fairchild Aircraft Corporation SA227 Series Service 
Bulletin No. 227-53-003, Issued: January 29, 1986, Revised: February 
13, 1986,
     Fairchild Aircraft Corporation SA226 Series Service 
Bulletin No. 226-53-007, Issued: May 7, 1981, Revised: February 17, 
1992,
     Fairchild Aircraft SA226/SA227 Structural Repair Manual 
(SRM) section 53-90-20, Initial Issue: March 1, 1983, Revision 24, 
dated August 27, 1997, and pages 2, 101, 102, 103, and 104;
     Fairchild Aircraft Approved Repair Procedure (ARP) 53-
30-9701, dated July 28, 1997.
    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, telephone (210) 824-9421. 
Copies may be inspected at the FAA, Central Region, Office of the 
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.
    (g) This amendment (39-10403) becomes effective on April 27, 
1998.

    Issued in Kansas City, Missouri, on March 9, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-6767 Filed 3-19-98; 8:45 am]
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