[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]
BILLING CODE 4910-13-U
