[Federal Register Volume 62, Number 5 (Wednesday, January 8, 1997)]
[Rules and Regulations]
[Pages 1044-1046]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-476]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-88-AD; Amendment 39-9869; AD 96-26-05]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 
400, 500, 600, and 700 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, 
and 700 series airplanes, that requires an inspection to detect 
cracking of the torque tube assembly of the left-hand (LH) elevator and 
surrounding structure; and to detect loose or sheared rivets in that 
assembly. This amendment also requires either replacement or repair of 
discrepant parts, as appropriate. This amendment is prompted by a 
report of fatigue cracking found on the torque tube support of the LH 
elevator. The actions specified by this AD are intended to ensure that 
cracking is detected and corrected in a timely manner so as to prevent 
failure of the torque tube or its support structure, which could result 
in reduced controllability of the airplane.

DATES: Effective February 12, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 12, 1997.
ADDRESSES: The service information referenced in this AD may be 
obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, 
Alexandria, Virginia 22314. This information may be examined at the 
Federal Aviation Administration (FAA), Transport

[[Page 1045]]

Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ruth Harder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-1721; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Fokker Model F27 Mark 100, 
200, 300, 400, 500, 600, and 700 series airplanes was published in the 
Federal Register on September 13, 1996 (61 FR 48439). That action 
proposed to require a one-time inspection to detect fatigue cracking of 
the torque tube of the left-hand (LH) elevator and its surrounding 
structure, and repair, if necessary. That action also proposed to 
require an inspection to detect loose or sheared rivets of the same 
torque tube assembly, and replacement with serviceable rivets, if 
necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 34 Fokker Model F27 Mark 100, 200, 300, 400, 
500, 600, and 700 series airplanes of U.S. registry will be affected by 
this AD, that it will take approximately 4 work hours per airplane to 
accomplish the required actions, and that the average labor rate is $60 
per work hour. Based on these figures, the cost impact of the AD on 
U.S. operators is estimated to be $8,160, or $240 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    Should an operator be required to replace the torque tube assembly 
of the LH elevator, the FAA estimates that it will take approximately 2 
work hours per airplane to accomplish, and that the average labor rate 
is $60 per work hour. Replacement of the assembly will cost 
approximately $1,500 per airplane. Based on these figures, the cost 
impact of the replacement is estimated to be $1,620 per airplane.

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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 the following new 
airworthiness directive:

96-26-05 Fokker: Amendment 39-9869. Docket 96-NM-88-AD.

    Applicability: All Model F27 Mark 100, 200, 300, 400, 500, 600, 
and 700 series airplanes, certificated in any category.

    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 (d) 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, unless accomplished 
previously.
    To ensure that cracking is detected and corrected in a timely 
manner so as to prevent failure of the torque tube of the left-hand 
(LH) elevator or its support structure, which could result in 
reduced controllability of the airplane, accomplish the following:
    (a) Prior to the accumulation of 45,000 total flight cycles, or 
within 4 months after the effective date of this AD, whichever 
occurs later, perform an inspection to detect cracking of the torque 
tube assembly and the surrounding structure of the LH elevator, and 
to detect any loose or sheared rivets of that assembly, in 
accordance with ``Part 1'' of the Accomplishment Instructions of 
Fokker Service Bulletin F27/55-66, dated December 21, 1994.
    (b) If no cracking is detected, and if no loose or sheared rivet 
is detected, during the inspection required by paragraph (a) of this 
AD: No further action is required by this AD.
    (c) If any discrepancy is detected during the inspection 
required by paragraph (a) of this AD: Accomplish the applicable 
requirements of paragraph (c)(1), (c)(2), or (c)(3) of this AD at 
the time specified in that paragraph, and in accordance with Fokker 
Service Bulletin F27/55-66, dated December 21, 1994.
    (1) If any cracking of the torque tube is detected, or if any 
loose or sheared rivet is detected: Prior to further flight, replace 
the discrepant part(s) in accordance with ``Part 2,'' paragraph A., 
of the Accomplishment Instructions of the service bulletin.

    Note 2: Fokker Service Bulletin F27/55-66 references Fokker 
Service Bulletin F27/55-40 as an additional source of service 
information for procedures to replace the torque tube assembly with 
a serviceable assembly.

    (2) If any cracking of the rib at station 300 is detected: Prior 
to further flight, repair in accordance with ``Part 2,'' paragraph 
B., of the Accomplishment Instructions of the service bulletin.
    (3) If any cracking in the torque tube support is detected: 
Prior to further flight, accomplish the requirements of either 
paragraph (c)(3)(i) or (c)(3)(ii) of this AD, as applicable.
    (i) If the crack length does not exceed 30 mm, stop drill the 
crack and, thereafter, repeat the inspection specified in paragraph 
(a) of this AD at intervals not to exceed 50 flight hours, in 
accordance with ``Part 2,'' paragraph C., of the Accomplishment 
Instructions of the service bulletin.

[[Page 1046]]

    (ii) If the crack length exceeds 30 mm, repair in accordance 
with a method approved by the Manager, Standardization Branch, ANM-
113.
    (d) 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, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, 
Standardization Branch, ANM-113.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (e) 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.
    (f) The actions shall be done in accordance with Fokker Service 
Bulletin F27/55-66, dated December 21, 1994. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, 
Alexandria, Virginia 22314. Copies may be inspected at the FAA, 
Transport Airplane Directorate, Alexandria, Virginia 22314. Copies 
may be inspected at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (g) This amendment becomes effective on February 12, 1997.

    Issued in Renton, Washington, on December 23, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-476 Filed 1-7-97; 8:45 am]
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