[Federal Register Volume 62, Number 199 (Wednesday, October 15, 1997)]
[Rules and Regulations]
[Pages 53532-53534]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27089]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-142-AD; Amendment 39-10156; AD 97-21-03]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe 125-800A Series 
Airplanes and Hawker 800 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 Raytheon Model BAe 125-800A series airplanes and 
Hawker 800 series airplanes, that requires a detailed visual inspection 
of the fuel feed hose assemblies of the auxiliary power unit (APU) to 
detect overheating, degradation, proper routing, and adequate 
clearance; and the correction of any discrepancies found. This 
amendment also requires modification of the fuel feed hose of the APU. 
This amendment is prompted by reports of heat damage to the fuel feed 
hose assembly of the APU due to contact between the hose assembly and 
hot surfaces. The actions specified by this AD are intended to prevent 
heat damage of the fuel feed hose, which could lead to a possible fire/
smoke hazard when failure of the hose assembly occurs and consequent 
fuel mist or spray is emitted into the rear equipment bay.

DATES: Effective November 19, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 19, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Manager Service Engineering, 
Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-
0085. 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 Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 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 Raytheon Model BAe 125-
800A series airplanes and Hawker 800 series airplanes was published as 
a supplemental notice of proposed rulemaking (NPRM) in the Federal 
Register on October 25, 1996 (61 FR 55233). That action proposed to 
require a detailed visual inspection of the fuel feed hose assemblies 
of the auxiliary power unit (APU) to detect overheating, degradation, 
proper routing, and adequate clearance; and the correction of any 
discrepancies found. That action also proposed to require modification 
of the fuel feed hose of the APU.

Consideration of Comments Received

    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.

Explanation of Change Made to the Proposal

    The FAA has revised the final rule to reflect the corporate name 
change of Beech Aircraft Corporation to Raytheon Aircraft Company.

[[Page 53533]]

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the change previously described. The FAA has determined that 
this change will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 70 Raytheon Model BAe 125-800A series 
airplanes and Hawker 800 series airplanes of U.S. registry will be 
affected by this AD. It will take approximately 2 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 
$8,400, or $120 per airplane.
    It will take approximately 4 work hours per airplane to accomplish 
the required modification, at an average labor rate of $60 per work 
hour. Required parts will cost approximately $218 per airplane. Based 
on these figures, the cost impact of the modification required by this 
AD on U.S. operators is estimated to be $32,060, or $458 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 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:

97-21-03  Raytheon Aircraft Company (Formerly Raytheon Aircraft 
Corporation; Beech Aircraft Corporation; Raytheon Corporate Jets, 
Inc.; British Aerospace, PLC; DeHavilland; Hawker Siddeley): 
Amendment 39-10156. Docket 95-NM-142-AD.

    Applicability: Model BAe 125-800A series airplanes (including 
military variants C-29A and U-125) and Hawker 800 series airplanes, 
constructor's numbers 8091 and subsequent; equipped with Turbomach 
auxiliary power unit (APU) (Modification 259404B); 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 (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 prevent heat damage to the fuel feed hose assemblies of the 
auxiliary power unit (APU), which could lead to a possible fire/
smoke hazard if failure of the hose assembly occurs and fuel mist or 
spar is consequently emitted into the rear equipment bay, accomplish 
the following:
    (a) Within 75 days after the effective date of this AD, perform 
a one-time detailed visual inspection to detect overheating or 
degradation of the hose assemblies; to verify proper routing of fuel 
feed hose assembly of the APU; and to verify if adequate clearance 
(0.5 inch) exists between the hose assembly (outlet from the fuel 
pump box of the APU) and the left-hand mixer valve/main air valve 
assemblies and associated hot air ducting; in accordance with Hawker 
Service Bulletin SB. 49-45, dated May 15, 1995.
    (1) If any overheating or degradation is detected, prior to 
further flight, replace the hose assembly with a new assembly and 
ensure that proper clearance and routing exists, in accordance with 
the service bulletin.
    (2) If the clearance of the hose assembly is improperly routed, 
prior to further flight, re-route the assembly maintaining proper 
clearance, in accordance with the service bulletin.
    (3) If the clearance of the hose assembly is inadequate and the 
hose assembly is properly routed, prior to further flight, adjust 
the hose assembly to achieve the 0.5-inch clearance, in accordance 
with the service bulletin.
    (b) Prior to the accumulation of 200 flight hours after the 
effective date of this AD, modify the fuel feed hose of the APU, in 
accordance with Hawker Service Bulletin SB.49-47-25A825A, dated 
August 1, 1995.
    (c) Accomplishment of the modification of the fuel feed hose of 
the APU in accordance with Hawker Service Bulletin SB.49-47-25A825A, 
dated August 1, 1995, constitutes terminating action for the 
requirements of this AD.
    (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 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.

    (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 Hawker Service 
Bulletin SB.49-45, dated May 15, 1995, and Hawker Service Bulletin 
SB.49-47-25A825A, dated August 1, 1995. The incorporation by 
reference of that document 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 Raytheon Aircraft Company, Manager 
Service Engineering, Hawker Customer Support Department, P.O. Box 
85, Wichita, Kansas 67201-0085. 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.


[[Page 53534]]


    Note 3: The subject of this AD is addressed in British 
airworthiness directive 005-05-95.

    (g) This amendment becomes effective on November 19, 1997.

    Issued in Renton, Washington, on October 7, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-27089 Filed 10-14-97; 8:45 am]
BILLING CODE 4910-13-U