AD Amdt-39-11151

[Federal Register Volume 64, Number 85 (Tuesday, May 4, 1999)]
[Rules and Regulations]
[Pages 23763-23766]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-10605]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-202-AD; Amendment 39-11151; AD 99-09-18]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark 
0100 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Fokker Model F.28 Mark 0070 and Mark 0100 
series

[[Page 23764]]

airplanes, that currently requires a one-time inspection for heat 
damage of the fuselage skin and stubwing structure; either repetitive 
tests of certain seals or repair of heat damage, as necessary; and 
eventual replacement of corrujoint seals with new, improved seals. This 
amendment adds a requirement for repetitive inspections for heat damage 
of the subject area, and provides for a new optional terminating action 
for the repetitive inspections. This action is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this AD are intended 
to prevent leakage of hot air from the corrujoint seals of certain 
valves in the stubwings, and subsequent heat damage of the fuselage 
skin and stubwing structure, which could result in reduced structural 
integrity of the airplane.

DATES: Effective June 8, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 8, 1999.
    The incorporation by reference of certain other publications as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of May 14, 1998 (63 FR 17318, April 9, 1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Fokker Services B.V., Technical Support Department, P.O. 
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. 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 Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-08-01, 
amendment 39 -10450 (63 FR 17318, April 9, 1998), which is applicable 
to certain Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, 
was published in the Federal Register on November 10, 1998 (63 FR 
62970). The action proposed to continue to require a one-time visual 
inspection to detect heat damage of the fuselage skin and stubwing 
structure; either repetitive leak tests of the seals of the bleed air 
system or repair of any heat-damaged structure, as necessary; and 
replacement of corrujoint seals with new, improved seals. Additionally, 
that action proposed to require repetitive inspections of the fuselage 
skin and stubwing connection angles to detect heat damage, and an 
additional detailed inspection of the fuselage and stubwing structure 
and repair when heat damage is detected. That action also proposed to 
provide for a new optional terminating action for the repetitive 
inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposal.

Request to Delay Requiring Repetitive Testing

    One commenter, an airline operator, requests that data derived from 
the initial inspection mandated by AD 98-08-01, which has a May 1999 
compliance time, be analyzed before a decision is made in regard to the 
need for additional testing.
    The commenter states that it has no objection to accomplishing the 
repetitive inspections specified in the proposal, if they are required. 
However, the commenter contends that mandating those repetitive 
inspections at this time would be acting prematurely, since all data 
from the initial inspections are not available to analyze.
    The FAA does not concur with the commenter's request to delay 
requiring repetitive inspections. The Rijksluchtvaartdienst (RLD), 
which is the airworthiness authority for the Netherlands, advised the 
FAA that a sufficient number of operators have already accomplished the 
one-time inspection described in Fokker Service Bulletin SBF100-53-084, 
dated July 6, 1996 (the referenced source of service information in the 
proposal and AD 98-08-01). Consequently, the RLD included requirements 
for repetitive inspections in Revision 3 of the Dutch airworthiness 
directive BLA 1995-076/3 (A), dated November 28, 1997, to ensure 
continued airworthiness. That revision is referenced in this AD.
    Therefore, the FAA has determined that the repetitive inspections 
required by this AD are necessary in order to adequately address the 
identified unsafe condition. However, as specified in paragraph (h) of 
this AD, operators have the option of modifying the airplane in 
accordance with Fokker Proforma Service Bulletin F100-36-027, dated 
March 21, 1997, which would provide terminating action for the 
repetitive inspection requirements of this AD.

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 as proposed.

Cost Impact

    There are approximately 141 Fokker Model F.28 Mark 0070 and Mark 
0100 series airplanes of U.S. registry that will be affected by this 
AD.
    The one-time visual inspection that is currently required by AD 98-
08-01, and retained in this AD, takes approximately 3 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the one-time inspection 
requirement of this AD on U.S. operators is estimated to be $180 per 
airplane.
    The seal replacement that is currently required by AD 98-08-01, and 
retained in this AD, takes approximately 7 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts cost approximately $80 per airplane. Based on these figures, the 
cost impact of the seal replacement requirement of this AD on U.S. 
operators is estimated to be $500 per airplane.
    The new actions that are required by this new AD will take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the new requirements of this AD on U.S. operators is 
estimated to be $25,380, or $180 per airplane, per inspection cycle.
    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.

[[Page 23765]]

    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 removing amendment 39-10450 (63 FR 
17318, April 9, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-11151, to read as follows:

99-09-18  Fokker Services B.V.: Amendment 39-11151. Docket 98-NM-
202-AD. Supersedes AD 98-08-01, Amendment 39-10450.

    Applicability: Model F.28 Mark 0070 and Mark 0100 series 
airplanes equipped with any corrujoint seal having part number (P/N) 
BE20061 (Rolls-Royce P/N 3405891) or on which Fokker Proforma 
Service Bulletin SBF100-36-027, including Appendix I, both dated 
March 21, 1997, has not been accomplished; certificated in any 
category.

    Note 1: This AD applies to each airplane 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 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 (i)(1) 
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 leakage of hot air from the corrujoint seals of the 
low- and high-pressure check valves located in the stubwings, and 
subsequent heat damage of fuselage skin and stubwing structure 
adjacent to bleed air system components in the stubwings, which 
could result in reduced structural integrity of the airplane, 
accomplish the following:

Restatement of Requirements of AD 98-08-01, Amendment 39-10450:

    (a) For Model F28 Mark 0070 and Mark 0100 series airplanes as 
listed in Fokker Service Bulletin SFB100-53-084, dated July 6, 1996; 
if equipped with any corrujoint seal having P/N BE20061 (Rolls-Royce 
P/N 3405891): Within 3,000 flight hours or 12 months after May 14, 
1998 (the effective date of AD 98-08-01, amendment 39-10450), 
whichever occurs first, perform a one-time visual inspection of the 
fuselage skin in the left- and right-hand stubwings to detect heat 
damage; in accordance with Part 2 of the Accomplishment Instructions 
of Fokker Service Bulletin SFB100-53-084, dated July 6, 1996.
    (b) If no heat damage is found during the inspection required by 
paragraph (a) of this AD, prior to further flight, accomplish either 
paragraph (b)(1) or (b)(2) of this AD.
    (1) Replace all corrujoint seals having P/N BE20061 (Rolls-Royce 
P/N 3405891) at the 7th stage low-pressure and 12th stage high-
pressure check valves of the left- and right-hand bleed air systems 
with new, improved corrujoint seals having P/N EU15969, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-36-026, Revision 1, dated July 6, 1996.
    (2) Perform a leak test of each corrujoint seal at the 7th stage 
low-pressure and 12th stage high-pressure check valves of the left- 
and right-hand bleed air systems, in accordance with Part 3 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-53-
084, dated July 6, 1996.
    (i) If any leakage is found at a seal, prior to further flight, 
replace that seal with a new, improved seal having part number 
EU15969, in accordance with the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-36-026, Revision 1, dated July 6, 
1996.
    (ii) If no leakage is found at a seal, perform an additional 
leak test of that seal within 250 flight hours after the initial 
test.
    (A) If no leakage is found during the additional test of the 
seal, within 3,000 flight hours after the additional test, replace 
the seal with an improved seal having P/N EU15969, in accordance 
with the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-36-026, Revision 1, dated July 6, 1996.
    (B) If any leakage is found during the additional test of the 
seal, prior to further flight, replace the seal with a new, improved 
seal having P/N EU15969, in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-36-026, Revision 1, 
dated July 6, 1996; and inspect the fuselage skin in the applicable 
left- or right-hand stubwing to detect heat damage, in accordance 
with Part 2 of the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-53-084, dated July 6, 1996.
    (c) If any heat damage is found during the inspection required 
by paragraph (a) or paragraph (b)(2)(ii)(B) of this AD, prior to 
further flight, perform a detailed inspection of the fuselage skin 
and stubwing structure to detect the extent of heat damage, in 
accordance with Parts 4 and 5 of the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-53-084, dated July 6, 1996; and 
accomplish paragraphs (c)(1) and (c)(2) of this AD.
    (1) Except as provided by paragraph (g) of this AD: Repair the 
affected structure in accordance with Part 6 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-53-084, dated July 6, 
1996. And
    (2) Replace all corrujoint seals having P/N BE20061 (Rolls-Royce 
P/N 3405891) at the 7th stage low-pressure and 12th stage high-
pressure check valves of the left- and right-hand bleed air systems 
with new, improved corrujoint seals having P/N EU15969, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-36-026, Revision 1, dated July 6, 1996.
    (d) As of May 14, 1998, no person shall install a corrujoint 
seal having P/N BE20061 (Rolls-Royce P/N 3405891) on any airplane.

New Requirements for This AD

    (e) For Model F.28 Mark 0070 and Mark 0100 series airplanes on 
which Fokker Proforma Service Bulletin SBF100-36-027, including 
Appendix I, both dated March 21, 1997, has not been accomplished: 
Perform a visual inspection of the fuselage skin in the left-and 
right-hand stubwings to detect heat damage, in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-53-
087, dated November 17, 1997, at the latest of the times specified 
in paragraphs (e)(1), (e)(2), and (e)(3) of this AD, as applicable. 
Repeat the inspection required by paragraph (e) of this AD 
thereafter at intervals not to exceed 6,000 landings.
    (1) Within 6,000 landings after the effective date of this AD.
    (2) Within 6 months after the effective date of this AD.
    (3) Within 6,000 landings after accomplishment of the inspection 
required by paragraph (a) of this AD.
    (f) If any heat damage is detected during any inspection 
required by paragraph (e) of this AD, prior to further flight, 
perform a detailed visual inspection to determine the extent of heat 
damage, in accordance with paragraph 2.B.(2) of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-53-087, dated 
November 17, 1997. Except as provided by paragraph (g) of this AD, 
prior to further flight, repair in accordance with the service 
bulletin.

    Note 2: Fokker Service Bulletin SBF100-53-087, dated November 
17, 1997, refers to

[[Page 23766]]

Fokker Service Bulletin SBF100-53-084, dated July 6, 1996, as an 
additional source of service information for the detailed inspection 
procedures, repair limits, and repair procedures.

    (g) If any damage is found during accomplishment of any action 
specified by paragraph (c)(1) or (f) of this AD, and Fokker Service 
Bulletin SBF100-53-084, dated July 6, 1996, or Fokker Service 
Bulletin SBF100-53-087, dated November 17, 1997, specifies to 
contact the manufacturer for an appropriate action: Prior to further 
flight, repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the RLD (or its delegated agent).
    (h) Installation of new heat shields, relocation of the aft bay 
overheat switch, and replacement of the insulation blankets of the 
bleed air ducts with new, improved insulation blankets, in 
accordance with Fokker Proforma Service Bulletin SBF100-36-027, 
including Appendix I, both dated March 21, 1997, constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (e) of this AD.

Alternative Method of Compliance

    (i)(1) 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, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 98-08-01, amendment 39-10450, are approved as 
alternative methods of compliance with paragraphs (a), (b), and (c) 
of this AD.
    (3) Airplanes repaired in accordance with alternative methods of 
compliance, approved previously in accordance with AD 98-08-01, 
amendment 39-10450, are not considered exempt from the repetitive 
inspection requirements of paragraph (e) of this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (j) 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

    (k) Except for the actions specified in paragraphs (g) and (h) 
of this AD, the actions shall be done in accordance with Fokker 
Service Bulletin SBF100-53-084, dated July 6, 1996; Fokker Service 
Bulletin SBF100-36-026, Revision 1, dated July 6, 1996; or Fokker 
Service Bulletin SBF100-53-087, dated November 17, 1997. The 
terminating action specified in paragraph (h) of this AD, if 
accomplished, shall be accomplished in accordance with Fokker 
Proforma Service Bulletin SBF100-36-027, including Appendix I, both 
dated March 21, 1997.
    (1) The incorporation by reference of Fokker Service Bulletin 
SBF100-53-087, dated November 17, 1997; and Fokker Proforma Service 
Bulletin SBF100-36-027, including Appendix I, both dated March 21, 
1997; is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Fokker Service Bulletin 
SBF100-53-084, dated July 6, 1996; and Fokker Service Bulletin 
SBF100-36-026, Revision 1, dated July 6, 1996; was approved 
previously by the Director of the Federal Register as of May 14, 
1998 (63 FR 17318, April 9, 1998).
    (3) Copies may be obtained from Fokker Services B.V., Technical 
Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the 
Netherlands. 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.

    Note 4: The subject of this AD is addressed in Dutch 
airworthiness directive 1995-076/3 (A), dated November 28, 1997.

    (l) This amendment becomes effective on June 8, 1999.

    Issued in Renton, Washington, on April 21, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-10605 Filed 5-3-99; 8:45 am]
BILLING CODE 4910-13-U