[Federal Register Volume 64, Number 95 (Tuesday, May 18, 1999)]
[Rules and Regulations]
[Pages 26831-26833]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-12098]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 64, No. 95 / Tuesday, May 18, 1999 / Rules
and Regulations
[[Page 26831]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-92-AD; Amendment 39-11169; AD 99-10-16]
RIN 2120-AA64
Airworthiness Directives; Mitsubishi Model YS-11 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 Mitsubishi Model YS-11 series airplanes, that
requires repetitive inspections to detect fatigue cracking in the
manhole doublers of the lower wing panels; and repair, if necessary.
This amendment also requires eventual modification of screw holes in
the manhole doublers of the lower wing panels, which constitutes
terminating action for the repetitive inspections required by this AD.
This amendment is prompted by the issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by this AD are intended to prevent fatigue
cracking in the manhole doublers of the lower wing panels, which could
result in failure of the wing structure.
DATES: Effective June 22, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 22, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-ku,
Nagoya 455, Japan. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
Transport Airplane Directorate, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5322; fax (562)
627-5210.
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 Mitsubishi Model YS-11 series
airplanes was published in the Federal Register on July 9, 1998 (63 FR
37080). That action proposed to require repetitive inspections to
detect fatigue cracking in the manhole doublers of the lower wing
panels; and repair, if necessary. That action also proposed to require
eventual modification of screw holes in the manhole doublers of the
lower wing panels.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request To Accept Modification as Terminating Action
Two commenters request that modification of the screw holes in the
manhole doublers of the lower wing panels, as described in NAMC Service
Bulletin 57-77, Revision 2, dated September 14, 1994, and specified in
paragraph (b) of the proposed AD, be considered terminating action for
the repetitive inspections described in paragraph (a) of the proposed
rule. ``NOTE 2'' of the proposed AD states, ``Accomplishment of the
modification specified in paragraph (b) does not constitute terminating
action for the repetitive inspections of paragraph (a).'' The
commenters state that repetitive inspections of the screw holes in the
manhole doublers of the lower wing panels are no longer necessary after
accomplishment of the modification, though inspection of the rivet
holes in the skin around the manhole, as specified in SID Item 57-00-
03, is still necessary.
The FAA concurs with the commenters' request to accept the
modification as terminating action for the repetitive inspections. The
FAA has reviewed Mitsubishi NAMC Service Bulletin 57-77, Revision 2,
and SID Item 57-00-03, and finds that repetitive inspections of the
screw holes in the manhole doublers of the lower wing panels are no
longer necessary after accomplishment of the modification specified in
the service bulletin. Therefore, paragraph (b) of this final rule has
been revised to eliminate reference to repair of any cracking detected
during repetitive inspections performed after accomplishment of the
modification, and to state that accomplishment of such modification
terminates the repetitive inspection requirement of this AD. In
addition, a reference to the modification as terminating action for the
repetitive inspections has been added to the ``Summary'' section of
this final rule. Also, ``NOTE 2'' of this final rule has been revised
to state, ``Mitsubishi NAMC Supplemental Inspection Document (SID) Item
57-00-03 describes inspections of certain rivet holes in the skin
around the manhole. Accomplishment of the modification specified in
paragraph (b) of this AD does not eliminate the need for the
inspections specified in that SID item.''
Request To Revise Address for Obtaining Service Information
One commenter requests that the proposed rule be revised to
reference the correct address from which service information may be
obtained. The commenter points out that Mitsubishi Heavy Industries,
not Nihon Aeroplane Manufacturing Company (NAMC) (which was referenced
as the appropriate source for the service information specified in the
proposal), provides technical publications for owners and operators of
Mitsubishi Model YS-11 series airplanes. The FAA concurs with the
commenter's request and has revised this final rule to reference the
correct address.
[[Page 26832]]
Request To Revise Information From NAMC Structural Inspection
Document
Two commenters request that the proposed AD be revised to more
accurately reflect the information in NAMC Supplemental Inspection
Document (SID) Item 57-00-03. The commenters point out that the
following statement in the preamble of the proposed AD under the
heading ``Differences Between Proposed Rule, Service Information, and
Japanese Airworthiness Directive'' is incorrect: ``Following
accomplishment of the modification described in the service bulletin,
the SID item specifies that the repetitive interval is reduced to 6,000
flight cycles.'' One of the commenters attributes the misstatement in
the proposed AD to a misunderstanding of a transmittal letter that
accompanied the SID. That commenter states that the change in
repetitive inspection interval referenced by the transmittal letter is
for a different inspection item within the SID (Inspection Item 57-00-
06), and the repetitive interval for the inspection in SID Item 57-00-
03 remains at 8,000 flight cycles.
The FAA acknowledges that the proposed AD could have more
accurately reflected the information in SID Item 57-00-03. However, the
proposed AD is unaffected by the statement in the preamble. Because the
section of the preamble that discusses the reduction of the repetitive
interval is not repeated in the final rule, no change to the final rule
is necessary in this regard.
Request To Revise Information From Japanese Airworthiness Directive
One commenter requests that the proposed rule be revised to reflect
the correct compliance date for the modification as specified in
Japanese Airworthiness Directive TCD-3795-2-96, dated December 13,
1996. Under the heading ``Differences Between Proposed Rule, Service
Information, and Japanese Airworthiness Directive,'' the proposed rule
states, `` * * * the Japanese airworthiness directive specifies that
modification of the screw holes in the manhole doublers of the lower
wing panels be accomplished prior to the accumulation of 60,000 total
flight cycles, or before December 13, 2000 (four years after the
effective date of the Japanese airworthiness directive), whichever
occurs later.'' The commenter states that, due to a mistranslation in
the English version of the AD, the date for required compliance is
incorrect. The commenter goes on to state that the correct compliance
date should be February 7, 1997, which is four years after the
effective date of the original Japanese airworthiness directive (TCD-
3795-93, dated February 7, 1993). The FAA acknowledges that a
mistranslation of the Japanese airworthiness directive occurred.
However, the proposed AD is unaffected by the statement in the
preamble. Because the subject section of the proposed rule is not
restated in the final rule, no change to the final rule is necessary in
this regard.
Request To Increase Repetitive Inspection Interval
One commenter requests that the repetitive inspection interval be
increased from 6,000 flight cycles, as specified in paragraph (a) of
the proposed AD, to 8,000 flight cycles. As described previously, the
commenter points out that SID Item 57-00-03 recommends a repetitive
inspection interval of 8,000 flight cycles.
The FAA does not concur with the commenter's request to increase
the repetitive inspection interval from 6,000 to 8,000 flight cycles.
In developing an appropriate compliance time for this AD, the FAA
considered not only the repetitive inspection interval specified in SID
Item 57-00-03, but also the degree of urgency associated with
addressing the subject unsafe condition (fatigue cracking in the
manhole doublers of the lower wing panels, which could result in
failure of the wing structure). In light of these factors, as well as
engineering judgement and experience, the FAA has determined that, due
to the safety implications and consequences associated with the
identified unsafe condition, a repetitive inspection interval that is
more conservative than the 8,000-flight-cycle interval recommended by
SID Item 57-00-03 is warranted. The FAA finds that an interval of 6,000
flight cycles will better ensure that any cracking of the manhole
doublers of the lower wing panels is detected and corrected in a timely
manner. No change to the final rule is necessary in this regard.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 25 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 30 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $45,000, or $1,800 per
airplane, per inspection cycle.
It will take approximately 40 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $60,000, or
$2,400 per airplane.
The cost impact figures discussed above are 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.
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
[[Page 26833]]
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:
99-10-16 Mitsubishi Heavy Industries, Ltd.: Amendment 39-11169.
Docket 97-NM-92-AD.
Applicability: All Model YS-11 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 (c) 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 prevent fatigue cracking in the manhole doublers of the lower
wing panels, which could result in failure of the wing structure,
accomplish the following:
Initial and Repetitive Inspections
(a) Perform a visual inspection to detect cracking in the
manhole doublers and around the screw holes of the lower wing
panels, in accordance with Mitsubishi Nihon Aeroplane Manufacturing
Company (NAMC) Service Bulletin 57-77, Revision 2, dated September
14, 1994, at the time specified in either paragraph (a)(1) or (a)(2)
of this AD, as applicable. Repeat the inspection thereafter at
intervals not to exceed 6,000 flight cycles.
(1) For airplanes that have accumulated fewer than 45,000 total
flight cycles as of the effective date of this AD: Prior to the
accumulation of 45,000 total flight cycles, or within 1 year after
the effective date of this AD, whichever occurs later, perform the
initial inspection.
(2) For airplanes that have accumulated 45,000 or more total
flight cycles as of the effective date of this AD: Within 2,000
flight cycles or 1 year after the effective date of this AD,
whichever occurs first, perform the initial inspection.
Modification
(b) Modify the screw holes in the manhole doublers of the lower
wing panels, in accordance with Mitsubishi NAMC Service Bulletin 57-
77, Revision 2, dated September 14, 1994, at the applicable time
specified in either paragraph (b)(1) or (b)(2) of this AD.
Accomplishment of such modification constitutes terminating action
for the repetitive inspections required by paragraph (a) of this AD.
Note 2: Mitsubishi NAMC Supplemental Inspection Document (SID)
Item 57-00-03 describes inspections of certain rivet holes in the
skin around the manhole. Accomplishment of the modification
specified in paragraph (b) of this AD does not eliminate the need
for the inspections specified in that SID item.
(1) If no cracking is found, prior to the accumulation of 60,000
total flight cycles, or within 1 year after the effective date of
this AD, whichever occurs later, accomplish the modification in
accordance with the service bulletin.
(2) If any cracking is found, prior to further flight, repair
the cracking and accomplish the modification, in accordance with the
service bulletin.
Alternative Methods of Compliance
(c) 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, Los Angeles Aircraft Certification
Office (ACO), 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, Los Angeles ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(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.
Incorporation by Reference
(e) The inspection and modification shall be done in accordance
with Mitsubishi Nihon Aeroplane Manufacturing Company (NAMC) Service
Bulletin 57-77, Revision 2, dated September 14, 1994, which contains
the following list of effective pages:
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Revision level shown
Page number on page Date shown on page
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1-3.................. 2..................... September 14, 1994.
4-16.................. 1..................... November 4, 1993.
17, 18................ Original.............. January 8, 1993.
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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 Mitsubishi Heavy Industries, Ltd.,
10 Oye-cho, Minato-ku, Nagoya 455, Japan. Copies may be inspected at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the FAA, Transport Airplane Directorate,
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
Note 4: The subject of this AD is addressed in Japanese
airworthiness directive TCD-3795-2-96, dated December 13, 1996.
(f) This amendment becomes effective on June 22, 1999.
Issued in Renton, Washington, on May 7, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-12098 Filed 5-17-99; 8:45 am]
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