[Federal Register Volume 61, Number 182 (Wednesday, September 18, 1996)]
[Rules and Regulations]
[Pages 49055-49056]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-23714]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-249-AD; Amendment 39-9758; AD 96-19-12]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Mark 0100 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 certain Fokker Model F28 Mark 0100 series airplanes, that
requires inspection and adjustment of the torque value of the attaching
parts of the interlock mechanism of the large cargo doors, removal of a
spring from that mechanism, and installation of a new microswitch
bracket. This amendment is prompted by a report indicating that a
spring on the interlock lever of the large cargo doors may become
disconnected or the lever may become jammed in the ``activated'' state.
The actions specified by this AD are intended to prevent the spring
from becoming disconnected or the lever from jamming. If other failures
occur, the flightcrew could dispatch the airplane with improperly
locked cargo doors; this condition could result in the opening and/or
separation of the cargo doors while the airplane is in flight and
subsequent rapid decompression and/or structural damage to the
airplane.
DATES: Effective October 23, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 23, 1996.
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 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: Tim Dulin, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2141; 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 certain Fokker Model F28 Mark 0100
series airplanes was published in the Federal Register on July 19, 1995
(60 FR 37038). For certain airplanes, that action proposed to require
an inspection to determine the torque value of the attaching parts of
the interlock mechanism of the large cargo doors, and adjustment of the
torque values that are outside certain limits. For other airplanes, the
action proposed to require removal of a spring from the interlock
mechanism of the large cargo doors, and installation of a new
microswitch bracket and two new springs in the interlock mechanism.
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 proposed rule.
Request for Extension of Compliance Time
One commenter requests that the compliance time for the proposed
actions be extended from the proposed 6 months to 12 months. This
commenter, a U.S. operator, states that its fleet includes 40 of the 61
U.S.-registered airplanes that would be affected by the rule. Extending
the compliance time to 12 months will allow the commenter to accomplish
the required modifications during a scheduled ``C'' check, when the
airplanes are brought to the main maintenance base for an extended
hold. Adoption of the proposed 6-month compliance time would require
that this commenter special-schedule its airplanes for the
accomplishment of the modification at stations other than the main
base; however, adoption of a 12-month compliance time would allow this
commenter's fleet to be modified at the same place and by the same
technicians familiar with the task.
The FAA does not concur with the commenter's request. In developing
an appropriate compliance time for this AD, the FAA considered not only
the safety implications, but the manufacturer's recommendations, the
Dutch airworthiness authority's recommendations, the availability of
required parts, and the practical aspect of accomplishing the
modification within an interval of time that parallels normal scheduled
maintenance for affected operators. The FAA also considered the fact
that the referenced Fokker service bulletin (containing the procedures
for accomplishing the required actions) has been available to all
operators of Fokker Model F28 Mark 0100 series airplanes since August
1993; therefore, U.S. operators have had ample time since then to
consider initiating those actions, which this AD ultimately mandates.
In light of all of these items, the FAA finds that 6 months is the
appropriate period of time that affected airplanes can be permitted to
continue to operate without compromising safety. Under the provisions
of paragraph (b) of the final rule, however, the FAA may consider
requests for adjustments to the compliance time if data are submitted
to substantiate that such an adjustment would provide an acceptable
level of safety.
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
The FAA estimates that 61 airplanes of U.S. registry will be
affected by this AD.
For 7 of these airplanes, it will take approximately 6 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 of these airplanes
is estimated to be $2,520, or $360 per airplane.
For the other 54 airplanes, it will take approximately 12 work
hours per airplane to accomplish the required removal and installation,
at an average labor rate of $60 per work hour. Required parts will cost
approximately $1,200 per airplane. Based on these figures, the cost
impact of the removal and installation required by this AD on U.S.
operators of these airplanes is estimated to be $103,680, or $1,920 per
airplane.
[[Page 49056]]
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 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:
96-19-12 Fokker: Amendment 39-9758. Docket 94-NM-249-AD.
Applicability: Model F28 Mark 0100 series airplanes; as listed
in Fokker Service Bulletin SBF100-52-045, dated August 25, 1993;
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 (b) 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 the opening and/or separation of the large cargo
doors while the airplane is in flight, which could result in rapid
decompression and/or structural damage to the airplane, accomplish
the following:
(a) Within 6 months after the effective date of this AD,
accomplish either paragraph (a)(1) or (a)(2) of this AD, as
applicable, in accordance with Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993.
(1) For airplanes having serial numbers listed in Part 1 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993: Perform an inspection to determine the
torque value of the attaching parts of the interlock mechanism of
the large cargo doors, in accordance with Part 1 of the
Accomplishment Instructions of the service bulletin. If the torque
value is outside the limits specified in paragraphs 2.C.(1) and
2.C.(2) of the Accomplishment Instructions of the service bulletin,
prior to further flight, adjust the torque value in accordance with
the service bulletin.
(2) For airplanes having serial numbers listed in Part 2 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-52-
045, dated August 25, 1993: Remove the spring from the interlock
mechanism, and install a new microswitch bracket and new springs in
the interlock mechanism, in accordance with Part 2 of the
Accomplishment Instructions of the service bulletin.
(b) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) 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.
(d) The actions shall be done in accordance with Fokker Service
Bulletin SBF100-52-045, dated August 25, 1993. 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, 1601 Lind Avenue, SW., Renton,
Washington; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on October 23, 1996.
Issued in Renton, Washington, on September 10, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-23714 Filed 9-17-96; 8:45 am]
BILLING CODE 4910-13-U
