[Federal Register Volume 63, Number 50 (Monday, March 16, 1998)]
[Rules and Regulations]
[Pages 12607-12609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6450]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-26-AD; Amendment 39-10383; AD 98-06-06]
RIN 2120-AA64


Airworthiness Directives; GKN Westland Helicopters Ltd., 30 
Series Helicopters

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 GKN Westland Helicopters Ltd. (Westland) 30 series 
helicopters. This action requires determining the total hours time-in-
service (TIS) of the six tail rotor drive shafts (drive shafts), 
creating a component history card or an equivalent record for each 
shaft, and replacing those drive shafts that exceed a certain TIS with 
an airworthy drive shaft. This amendment is prompted by findings of 
drive shaft attachment flange cracks on similar British military model 
helicopters. This condition, if not corrected, could result in failure 
of the drive shaft coupling attachment flanges that could result in 
loss of power to the tail rotor and subsequent loss of control of the 
helicopter.

DATES: Effective March 31, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 31, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before May 15, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-26-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    The service information referenced in this AD may be obtained from 
GKN Westland Helicopters Ltd., Customer Support Division, Yeovil, 
Somerset BA20 2YB, England, telephone (01935) 703884, fax (01935) 
703905. 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: Mr. Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, ASW-111, 2601 Meacham Blvd., Fort Worth, 
Texas 76137, telephone 817-222-5296, fax 817-222-5961.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the FAA that an unsafe condition may exist on Westland 30 
series helicopters. The UK CAA advises that two incidents of drive 
shaft attachment flange cracking occurred on the Lynx model 
helicopters, the UK military version of the Westland 30 helicopters. 
Consequently, the appropriate drive shaft lives for the Westland 30 
series helicopters have been reconsidered.
    Westland has issued GKN Westland Helicopters Ltd. Service Bulletin 
(SB) Nos. W30-65-48, dated November 29, 1995, and W30-65-48, Annex A, 
dated November 8, 1996, which specify the procedure to establish the 
current TIS of the Westland 30 series helicopters' drive shafts, the 
hours at which the drive shafts should be replaced or inspected, and 
the inspection procedure. The UK CAA classified these SB's as mandatory 
and issued UK CAA AD 013-11-95, dated January 31, 1996, to ensure the 
continued airworthiness of these helicopters in the UK.
    These helicopter models, manufactured in Yeovil, England, are type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the UK CAA has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the UK CAA, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Westland 30 series helicopters of the same 
type design eligible for registration in the United States, this AD is 
being issued to prevent failure of the drive shaft coupling attachment 
flanges that could result in loss of power to the tail rotor and the 
subsequent loss of control of the helicopter. This AD requires that the 
TIS of each of the six drive shafts be determined from the helicopter 
records and that a component history card or an equivalent record be 
created for each drive shaft. If drive shaft No. 1, 2, 3, 4, or 5 
exceeds 1,000 hours TIS or drive shaft No. 6 exceeds 500 hours TIS,

[[Page 12608]]

replacement with an airworthy drive shaft in accordance with the SB is 
required. Alternatively, inspection of any drive shaft (No. 1, 2, 3, 4, 
or 5) with over 1,000 hours TIS and drive shaft No. 6 with over 500 
hours TIS is required in accordance with GKN Westland Helicopters Ltd. 
SB No. W30-65-48, paragraph 2.B.(3), dated November 29, 1995, prior to 
further flight and thereafter at intervals not to exceed 3 hours TIS. 
The actions are required to be accomplished in accordance with the SB's 
previously described.
    None of the Westland 30 series helicopters affected by this action 
are on the U.S. Register. All helicopters included in the applicability 
of this rule are currently operated by non-U.S. operators under foreign 
registry; therefore, they are not directly affected by this AD action. 
However, the FAA considers this rule necessary to ensure that the 
unsafe condition is addressed in the event that any of these subject 
helicopters are imported and placed on the U.S. Register in the future.
    Should an affected helicopter be imported and placed on the U.S. 
Register, it will require approximately 2 work hours to accomplish each 
required inspection at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of this AD will be $1200 per 
helicopter for accomplishment of 10 drive shaft flange inspections.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. Register, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, it is found that 
notice and opportunity for prior public comment hereon are unnecessary, 
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 should 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 No. 97-SW-26-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 notice and public comment are 
unnecessary in promulgating this regulation, that the regulation can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States, 
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 a new airworthiness directive 
to read as follows:

AD 98-06-06  GKN Westland Helicopters Ltd.: Amendment 39-10383. 
Docket No. 97-SW-26-AD.

    Applicability: Westland 30 Series Helicopters, certificated in 
any category.

    Note 1: This AD applies to each helicopter 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 helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (e) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any aircraft from the applicability of this AD.
    Compliance: Required as indicated, unless previously 
accomplished.
    To prevent failure of the tail rotor drive shaft (drive shaft) 
coupling attachment flanges that could lead to loss of tail rotor 
drive and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Within 7 calendar days after the effective date of this AD:
    (1) Determine from the helicopter records the total hours time-
in-service (TIS) for drive shaft number (No.) 1, 2, 3, 4, 5, and 6.
    (2) Create a component history card or an equivalent record for 
each drive shaft in accordance with paragraph 2.A.(2) of GKN 
Westland Helicopters Ltd. Service Bulletin No. W30-65-48, dated 
November 29, 1995.
    (b) Before further flight and at intervals not to exceed 3 hours 
TIS thereafter, inspect the drive shaft attachment flanges for 
cracks in accordance with paragraph 2.B.(3) of the Accomplishment 
Instructions of GKN Westland Helicopters, Ltd. Service Bulletin (SB) 
W30-65-48, dated November 29, 1995, as follows:
    (1) Drive shaft No. 1, 2, 3, 4, or 5 that has exceeded 1,000 
hours TIS;
    (2) Drive shaft No. 6 that has exceeded 500 hours TIS; and
    (3) Any drive shaft identified by serial number or flange serial 
number in Annex A to GKN Westland Helicopter, Ltd. SB W30-65-48, 
dated November 8, 1996, that has exceeded 500 hours TIS.

[[Page 12609]]

    No more than 10 repetitive inspections are permitted for any 
affected drive shaft.
    (c) If a crack is found as a result of the inspections required 
by paragraph (b) of this AD, before further flight, replace the 
drive shaft with an airworthy drive shaft.
    (d) Before further flight, or after 10 repetitive inspections 
have been accomplished, replace with an airworthy drive shaft any 
drive shaft that has reached or exceeded the applicable TIS stated 
in paragraph (b) of this AD.
    (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, Rotorcraft Standards Staff, 
Rotorcraft Directorate. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff, 
Rotorcraft Directorate.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (f) Special flight permits will not be issued.
    (g) The inspection shall be done in accordance with GKN Westland 
Helicopters Ltd. Service Bulletin No. W30-65-48, dated November 29, 
1995, and Annex A, dated November 8, 1996. 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 GKN Westland Helicopters Ltd., Customer Support 
Division, Yeovil, Somerset BA20 2YB, England, telephone (01935) 
703884, fax (10935) 703905. Copies may be inspected at the FAA, 
Office of 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.
    (h) This amendment becomes effective on March 31, 1998.

    Note 3: The subject of this AD is addressed in Civil Aviation 
Authority (United Kingdom) AD 013-11-95, dated January 31, 1996.

    Issued in Fort Worth, Texas, on March 4, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-6450 Filed 3-13-98; 8:45 am]
BILLING CODE 4910-13-U