[Federal Register Volume 68, Number 84 (Thursday, May 1, 2003)]
[Rules and Regulations]
[Pages 23190-23192]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-10507]



[[Page 23190]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-57-AD; Amendment 39-13134; AD 2003-09-05]
RIN 2120-AA64


Airworthiness Directives; Schweizer Aircraft Corporation Model 
269D Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters. This 
action requires inspecting each aluminum horizontal stabilizer endplate 
(endplate) and the attach angles for cracks, fretting, and endplate 
bending. If fretting is found, as indicated by a powder residue 
adjacent to a rivet head, installing an inspection hole in the 
horizontal stabilizer and inspecting the internal structure is 
required. Replacing unairworthy parts is required before further 
flight. Finally, reporting any cracked or bent endplate, any cracked 
attach angles, or fretting to the FAA is required. This amendment is 
prompted by reports of loose endplates, and one report of an endplate 
separating from the helicopter during flight. The actions specified in 
this AD are intended to prevent loss of an endplate during flight, 
which could strike the tail rotor and result in loss of control of the 
helicopter.

DATES: Effective May 16, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 16, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before June 30, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-57-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].
    The service information referenced in this AD may be obtained from 
Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. 
This information may be examined at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: George Duckett, Aviation Safety 
Engineer, FAA, New York Aircraft Certification Office, Airframe and 
Propulsion Branch, 10 Fifth Street, 3rd Floor, Valley Stream, New York, 
telephone (516) 256-7525, fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Schweizer 
Model 269D helicopters. This action requires inspecting each aluminum 
endplate and the attach angles for cracks, fretting, and endplate 
bending before further flight, and thereafter at each 100-hour 
inspection. Installing an inspection hole in the horizontal stabilizer 
and inspecting the internal structure is required before further flight 
if fretting is found, as indicated by a powder residue adjacent to a 
rivet head. If no powder residue is found, then installing an 
inspection hole is required at the next 100-hour inspection. Replacing 
unairworthy parts is required before further flight. Schweizer Basic 
Handbook of Maintenance Instructions (HMI), dated December 9, 2002, 
pertains to the subject of this AD. Section 11 of the HMI describes the 
inspection and replacement procedures. Reporting any cracked or bent 
endplate, any cracked attach angles, or fretting to the FAA is required 
within one day of the inspection. The report must include the 
helicopter model, configuration, and serial number; description of the 
damage; the TIS of the damaged part; and the TIS since the last 100-
hour TIS inspection. This amendment is prompted by reports of loose 
endplates, and one report of an endplate separating from the helicopter 
during flight. There are two types of endplates currently in service: 
an aluminum honeycomb endplate, part number (P/N) 269D3413-11, and a 
fiberglass honeycomb endplate, P/N 269D3413-13. The reports of 
difficulties have been limited to the aluminum endplates. The actions 
specified in this AD are intended to prevent loss of an endplate during 
flight, which could strike the tail rotor and result in loss of control 
of the helicopter.
    The FAA has reviewed Schweizer Service Bulletin No. DB-011.1, dated 
March 20, 2003, which describes procedures for inspecting the 
horizontal stabilizer, endplate, and attach angles, and installing an 
inspection hole in the horizontal stabilizer.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent loss of an endplate during flight, which could strike the 
tail rotor and result in loss of control of the helicopter. This AD 
requires inspecting each aluminum endplate for a crack or bending, and 
inspecting each attach angle for cracks or fretting. If fretting is 
found, as indicated by a powder residue adjacent to a rivet head, 
installing an inspection hole in the horizontal stabilizer and 
inspecting the internal structure is required. Replacing unairworthy 
parts is required before further flight. Finally, reporting any cracked 
or bent endplate, any cracked attach angles, or fretting to the FAA is 
required within one day of the inspection. The report must include the 
helicopter model, configuration, and serial number; the TIS of the 
damaged part; and the TIS since the last 100-hour TIS inspection. The 
actions must be accomplished in accordance with the service bulletin 
described previously. The short compliance time involved is required 
because the previously described critical unsafe condition can 
adversely affect the controllability and structural integrity of the 
helicopter. Therefore, inspecting the horizontal stabilizer, endplate 
and attach angles and replacing parts, if necessary, is required before 
further flight and this AD must be issued immediately.
    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.
    The FAA estimates that 22 helicopters will be affected by this AD, 
that it will take approximately: 0.5 work hour to inspect the exterior 
of the horizontal stabilizer and endplate; 0.5 work hour to inspect the 
interior of the horizontal stabilizer; 1.5 work hours to cut an 
inspection hole and make a cover plate; and 4.5 work hours to replace a 
rib, two angles, a doubler, and an endplate. The average labor rate is 
$60 per work hour. Required parts will cost approximately $20 for the 
access cover and $1,380 per side for the rib, two angles, doubler, 
endplate, and fasteners, per helicopter. Based on these figures, and 
assuming 7 helicopters (approximately one-third of the inspected 
helicopters) will require one endplate replacement on one side, the 
total cost impact of the AD on U.S. operators is estimated to be 
$15,290.

[[Page 23191]]

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 should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
comments 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 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 No. 2002-SW-57-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-09-05 Schweizer Aircraft Corporation: Amendment 39-13134. 
Docket No. 2002-SW-57-AD.

    Applicability: Model 269D helicopters, serial numbers 0001 
through 0022, with an aluminum horizontal stabilizer endplate 
(endplate), part number (P/N) 269D3413-11, installed, certificated 
in any category.

    Note 1: This AD applies to each helicopter 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 helicopters 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.


    Note 2: There are two types of endplates currently in service: 
an aluminum honeycomb endplate, part number (P/N) 269D3413-11, that 
is approximately 0.2 inches thick, and a fiberglass honeycomb 
endplate, P/N 269D3413-13, that is approximately 0.3 inches thick.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of an endplate during flight, which could strike 
the tail rotor and result in loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight, and thereafter at each 100-hour 
inspection, inspect each endplate and the attach angles in 
accordance with the Procedure, Part I, of Schweizer Service Bulletin 
No. DB-011.1, dated March 20, 2003 (SB).
    (1) If an endplate is bent or a crack is found in an endplate or 
an attach angle, before further flight, replace the attach angles 
and tip rib with new, airworthy parts and replace the endplate with 
a new, airworthy endplate, P/N 269D3413-13.
    (2) If fretting is found, as indicated by a powder residue 
adjacent to a rivet head in an attach angle, before further flight:
    (i) Install an inspection hole in the bottom of the horizontal 
stabilizer in accordance with the Procedure, Part II, of the SB,
    (ii) Inspect the internal structure of the horizontal 
stabilizer, and
    (iii) Replace all unairworthy parts.

    Note 3: Schweizer Basic Handbook of Maintenance Instruction 
(HMI), dated December 9, 2002, pertains to the subject of this AD.

    (b) If no powder residue is found, install an inspection hole in 
the bottom of the horizontal stabilizer in accordance with the 
Procedure, Part II, of the SB at the next 100-hour inspection.
    (c) If a cracked or bent endplate, any cracked attach angles, or 
fretting is found, report that damage to the FAA, ATTN: George 
Duckett, within one day. Reports may be faxed to (516) 568-2716, or 
emailed to [email protected]. Report the helicopter model, 
configuration, serial number, description of the damage, the TIS of 
the damaged part, and the TIS since the last 100-hour TIS 
inspection.
    (d) Information collection requirements contained in this AD 
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.
    (e) 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, New York Aircraft Certification 
Office (NYACO), FAA. Operators shall submit their requests through 
an FAA Principal Maintenance Inspector, who may concur or comment 
and then send it to the Manager, NYACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the NYACO.

    (f) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (g) The inspections and modifications, if necessary, shall be 
done in accordance with Schweizer Service Bulletin No. DB-011.1, 
dated March 20, 2003. 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 Schweizer 
Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies 
may be inspected at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 
or at the Office of the Federal

[[Page 23192]]

Register, 800 North Capitol Street, NW., suite 1700, Washington, DC.
    (h) This amendment becomes effective on May 16, 2003.

    Issued in Fort Worth, Texas, on April 22, 2003.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-10507 Filed 4-30-03; 8:45 am]
BILLING CODE 4910-13-P