AD Amdt-39-9913

[Federal Register Volume 62, Number 23 (Tuesday, February 4, 1997)]
[Rules and Regulations]
[Pages 5143-5145]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-2518]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-258-AD; Amendment 39-9913; AD 97-03-07]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Hawker 800 and 1000 and 
Model DH/BH/HS/BAe 125 Series Airplanes (Including Major Variants C29A, 
U125, and U125A 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 Raytheon Model BAe 125-1A through -1000A 
series airplanes and Model Hawker 800 and 1000 airplanes, that 
currently requires repetitive inspections to detect fatigue cracking of 
the sidestay jack pivots of the main landing gear (MLG), and 
replacement of the sidestay jack pivot assemblies with new assemblies. 
This amendment adds a requirement to replace the sidestay jack pivot 
assemblies with new, improved assemblies; when accomplished, this 
replacement would terminate the inspection requirements of the AD. This 
amendment also expands the applicability of the existing AD to include 
additional airplanes. The actions specified by this AD are intended to 
prevent fatigue fracturing of the sidestay jack pivots of the MLG, 
which could result in the inability of the MLG to deploy and a 
consequent wheels-up landing.

DATES: Effective March 11, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 11, 1997.
    The incorporation by reference of Raytheon Corporate Jets Service 
Bulletin SB 32-233, dated June 24, 1994, listed in the regulations, was 
approved previously by the Director of the Federal Register as of 
February 3, 1995 (60 FR 330, January 4, 1995).

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 (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-26-12, 
amendment 39-9107 (60 FR 330, January 4, 1995), which is applicable to 
certain Raytheon Model BAe 125-1A through -1000A series airplanes and 
Model Hawker 800 and 1000 airplanes, was published in the Federal 
Register on October 18, 1996 (61 FR 54359). The action proposed to 
expand the applicability of the existing AD to include additional 
airplanes. It also proposed to require installation of new, improved 
sidestay jack pivot assemblies, which would constitute terminating 
action for the inspection requirements of this AD.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No

[[Page 5144]]

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

    There are approximately 550 Raytheon Model BAe 125-1 through 1000A 
series airplanes and Model Hawker 1000 airplanes of U.S. registry that 
will be affected by this proposed AD.
    The actions that are currently required by AD 94-26-12 take 
approximately 6 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. The manufacturer is currently 
supplying required parts at no cost to the operators. Based on these 
figures, the cost impact of the previously required actions on U.S. 
operators is estimated to be $198,000, or $360 per airplane, per 
inspection cycle.
    The new (replacement) actions that are required by this new AD will 
take approximately 4 work hours per airplane to accomplish, 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 new requirements of this AD on U.S. operators is 
estimated to be $792,000, or $1,440 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 removing amendment 39-9107 (60 FR 
330, January 4, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-9913, to read as follows:

97-03-07  Raytheon Aircraft Company (Formerly Beech, Raytheon 
Corporate Jets, British Aerospace, Hawker Siddley, et al.): 
Amendment 39-9913. Docket 95-NM-258-AD. Supersedes AD 94-26-12, 
Amendment 39-9107.

    Applicability: Model Hawker 800 and 1000 and Model DH/BH/HS/BAe 
125 series airplanes (including major variants C29A, U125, and U125A 
series airplanes); equipped with main landing gear (MLG) sidestay 
assemblies on which Post-Mod 252091 steel jack pivots have been 
installed; 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 (f) 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.
    Note 2: Raytheon Model BAe 125 series 800B and BAe 125-1000B 
airplanes are similar in design to the airplanes that are subject to 
the requirements of this AD and, therefore, also may be subject to 
the unsafe condition addressed by this AD. However, as of the 
effective date of this AD, those models are not type certificated 
for operation in the United States. Airworthiness authorities of 
countries in which the Model BAe 125 series 800B and BAe 125-1000B 
airplanes are approved for operation should consider adopting 
corrective action, applicable to those models, that is similar to 
the corrective action required by this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the inability of the MLG to deploy and a consequent 
wheels-up landing, accomplish the following:

    Note 3: Paragraph (a) of this AD restates the requirements of AD 
94-26-12. As allowed by the phrase, ``unless accomplished 
previously,'' if the initial inspection required by that AD has been 
accomplished previously, paragraph (a) of this AD does not require 
that initial inspection to be repeated.

    (a) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG 
sidestay assemblies on which Post-Mod 252091 steel jack pivots have 
been installed, except for airplanes as specified in paragraph (d) 
of this AD: Perform a detailed visual inspection, using a 10X 
magnifier, to detect cracking of the sidestay assembly jack pivot of 
the left and right MLG, in accordance with Raytheon Corporate Jets 
Service Bulletin SB 32-233, dated June 24, 1994; Revision 1, dated 
July 8, 1994; or Revision 2, dated July 28, 1995; at the latest of 
the times specified in paragraph (a)(1), (a)(2), or (a)(3) of this 
AD.
    (1) Within 28 days after February 3, 1995 (the effective date of 
AD 94-26-12, Amendment 39-9107); or
    (2) Prior to the accumulation of 3,000 total landings on the 
sidestay assembly since new; or
    (3) Prior to the accumulation of 1,000 total landings since 
overhaul of the sidestay assembly.
    (b) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG 
sidestay assemblies on which Post-Mod 252091 steel jack pivots (part 
numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been installed 
prior to June 24, 1994, except for airplanes as specified in 
paragraph (d) of this AD:
    (1) If no cracks are found during the inspection required by 
paragraph (a) of this AD, and the sidestay assembly has been 
overhauled prior to the accomplishment of the inspection, accomplish 
the requirements of paragraphs (b)(1) and (b)(2) of this AD at the 
times specified.
    (i) Repeat the inspection specified in paragraph (a) of this AD 
within 1,000 landings after accomplishing the initial inspection, 
and thereafter at intervals not to exceed 1,000 landings, in 
accordance with Raytheon Corporate Jets Service Bulletin SB 32-233, 
dated June 24, 1994; Revision 1, dated July 8, 1994; or Revision 2, 
dated July 28, 1995.
    (ii) Prior to the accumulation of 4,000 total landings on the 
jack pivot assembly since the sidestay assembly was new or last 
overhauled, or within 300 landings after the effective date of this 
AD, whichever occurs

[[Page 5145]]

later: Replace the jack pivot assembly with a new, improved 
assembly, in accordance with Raytheon Corporate Jets Service 
Bulletin SB.32-233-3597A, dated July 28, 1995. Accomplishment of 
this replacement constitutes terminating action for the inspection 
requirements of this AD.
    (2) If no cracks are found during the inspection required by 
paragraph (a) of this AD, and the sidestay assembly has not been 
overhauled prior to accomplishment of that inspection: Prior to the 
accumulation of 4,000 total landings on the jack pivot assembly, or 
within 300 landings after the effective date of this AD, whichever 
occurs later, replace the jack pivot assembly with a new, improved 
assembly, in accordance with Raytheon Corporate Jets Service 
Bulletin SB 32-233, Revision 2, dated July 28, 1995. Accomplishment 
of this replacement constitutes terminating action for the 
inspection requirements of this AD.
    (c) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG 
sidestay assemblies on which Post-Mod 252091 steel jack pivots (part 
numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been installed on 
June 24, 1994, or later, except for airplanes as specified in 
paragraph (d) of this AD: Replace the jack pivot assembly with a 
new, improved assembly in accordance with Raytheon Corporate Jets 
Service Bulletin SB.32-233-3597A, dated July 28, 1995, at the later 
of the times specified in paragraph (c)(1) or (c)(2) of this AD. 
Accomplishment of this replacement constitutes terminating action 
for the inspection requirements of this AD.
    (1) Prior to the accumulation of 2,000 total landings since 
installation of Post Mod 252091 steel jack pivots. Or
    (2) Within 1,000 landings after the effective date of this AD.
    (d) For all Raytheon Model BAe 125 Series 800A C29A, U125, and 
Hawker 800 U125A airplanes on which Post Mod 252091 steel jack 
pivots (part numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been 
installed: Accomplish paragraphs (d)(1) and (d)(2) of this AD at the 
times specified in those paragraphs.
    (1) Perform a detailed visual inspection, using a 10X magnifier, 
to detect cracking of the sidestay assembly jack pivot of the left-
and right-hand MLG, in accordance with Raytheon Corporate Jets 
Service Bulletin SB 32-233, Revision 2, dated July 28, 1995, at the 
later of the times specified in paragraph (d)(1)(i) or (d)(1)(ii) of 
this AD. Thereafter, repeat this inspection at intervals not to 
exceed 200 landings, until the requirements of paragraph (d)(2) of 
this AD are accomplished.
    (i) Prior to the accumulation of 1,200 total landings since the 
installation of a steel jack pivot (Post Mod 252091). Or
    (ii) Within 56 days or within 200 landings after the effective 
date of this AD, whichever occurs first.
    (2) Prior to the accumulation of 2,000 total landings on the 
jack pivot, or within 300 landings after the effective date of this 
AD, whichever occurs later: Replace the sidestay jack pivot assembly 
with a new, improved assembly (part numbers 25UM1335-1A and 25-
8UM173-1A) in accordance with Raytheon Corporate Jets Service 
Bulletin SB.32-233-3597A, dated July 28, 1995. Accomplishment of 
this replacement constitutes terminating action for the inspection 
requirements of this AD.
    (e) If any crack is detected during any inspection required by 
this AD, replace the sidestay jack pivot assembly with a new, 
improved assembly (part numbers 25UM1335-1A and 25-8UM173-1A) in 
accordance with Raytheon Corporate Jets Service Bulletin SB.32-233-
3597A, dated July 28, 1995, at the time specified in paragraph 
(e)(1) or (e)(2) of this AD, as applicable. Accomplishment of this 
replacement constitutes terminating action for the inspection 
requirements of this AD.
    (1) For airplanes on which a crack is detected that does not 
exceed the limits specified in the service bulletin, replace the 
assembly at the later of the times specified in paragraph (e)(1)(i) 
or (e)(1)(ii) of this AD.
    (i) Within 100 landings after the effective date of this AD. Or;
    (ii) Within 100 landings after the initial detection of the 
cracking.
    (2) For airplanes on which a crack is detected that exceeds the 
limits specified in the service bulletin, prior to further flight, 
replace the assembly in accordance with the service bulletin.
    (f) 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, 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (g) 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.
    (h) The actions shall be done in accordance with the following 
Raytheon Corporate Jets service bulletins, which contain the 
specified list of effective pages:

----------------------------------------------------------------------------------------------------------------
 Service bulletin referenced and                                Revision level shown on                         
              date                          Page No.                      page              Date shown on page  
----------------------------------------------------------------------------------------------------------------
SB 32-233, June 24, 1994........  1-10........................  Original...............  June 24, 1994.         
SB 32-233 Revision 1, July 8,     1, 2, 5.....................  1......................  July 8, 1994.          
 1994.                            3, 4, 6-10..................  Original...............  June 24, 1994.         
SB 32-233 Revision 2, July 28,    1-4, 6, 7, 9................  2......................  July 28, 1995.         
 1995.                            5...........................  1......................  July 8, 1994.          
                                  8, 10.......................  Original...............  June 24, 1994.         
SB.32-233-3597A, July 28, 1995..  1-8.........................  Original...............  July 28, 1995.         
----------------------------------------------------------------------------------------------------------------

The incorporation by reference of Raytheon Corporate Jets Service 
Bulletin SB 32-233, dated June 24, 1994, was approved previously by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51 as of February 3, 1995 (60 FR 330, January 
4, 1995). The incorporation by reference of the remainder of the 
service documents listed above is 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.

    (i) This amendment becomes effective on March 11, 1997.

    Issued in Renton, Washington, on January 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-2518 Filed 2-3-97; 8:45 am]
BILLING CODE 4910-13-U