[Federal Register Volume 61, Number 203 (Friday, October 18, 1996)]
[Proposed Rules]
[Pages 54359-54362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26710]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 61, No. 203 / Friday, October 18, 1996 / 
Proposed Rules  

[[Page 54359]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-258-AD]
RIN 2120-AA64


Airworthiness Directives; Beech (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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Beech (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 action would add 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 proposal also would expand the 
applicability of the existing AD to include additional airplanes. The 
actions specified by this proposed 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: Comments must be received by November 26, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-258-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule 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 FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 95-NM-258-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 95-NM-258-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On December 21, 1994, the FAA issued AD 94-26-12, amendment 39-9107 
(60 FR 330, January 4, 1995), applicable to Beech (Raytheon) Model BAe 
125-1A through-1000A series airplanes and Model Hawker 800 and 1000 
airplanes equipped with main landing gear (MLG) sidestay assemblies on 
which Post-Mod 252091 steel jack pivots have been installed. That AD 
requires a detailed visual inspection to detect cracking of the 
sidestay jack pivots of the MLG and repair, if necessary. In addition, 
that AD requires eventual replacement of the sidestay jack pivot 
assemblies with new assemblies. The critical fatigue load on the 
sidestay jack pivot occurs during the deployment and retraction of the 
MLG. That action was prompted by a report of fracturing of a jack 
pivot, which resulted in the inability of the MLG to deploy. The 
requirements of that AD are intended to prevent a wheels-up landing.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the manufacturer has issued Service 
Bulletin SB 32-233, Revision 2, dated July 28, 1995, which adds certain 
major variant airplanes to the effectivity listing of the service 
bulletin. Because these variant airplanes perform a greater number of 
deployments and retractions of the MLG than other airplanes, the 
sidestay jack pivots are exposed to more fatigue cycles per flight. 
Consequently, the service bulletin recommends a reduction of the 
inspection threshold and repetitive inspection intervals for these 
airplanes until replacement with new, improved sidestay jack pivot 
assemblies is accomplished.
    This service bulletin also describes a schedule to replace the 
sidestay jack pivots with new, improved assemblies for certain 
airplanes on which Modification 252091 (the installation of a steel 
pivot with an eccentric bush) was installed after June 23, 1994. Those 
assemblies installed after June 23, 1994, were manufactured with a 
defective

[[Page 54360]]

surface finish. Identification of the installation date of the assembly 
is the only way to determine if the assembly was manufactured with the 
defective surface finish.
    Additionally, the manufacturer has issued Service Bulletin SB. 32-
233-3597A, dated July 28, 1995. This service bulletin describes 
procedures for replacement of the sidestay jack pivot assembly with a 
new, improved assembly. The new sidestay jack pivot assembly has an 
increased radii and local shot peening to further improve the fatigue 
performance. Accomplishment of this replacement eliminates the need for 
repetitive inspection and replacement of the sidestay jack pivot 
assemblies with the existing assemblies.
    The Civil Aviation Authority (CAA) classified both of these service 
bulletins as mandatory in order to assure the continued airworthiness 
of these airplanes in the United Kingdom.

FAA's Conclusions

    These airplane models are manufactured in the United Kingdom and 
are type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral airworthiness agreement, the CAA has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 94-26-12 to 
continue to require inspections to detect cracking of the sidestay jack 
pivots of the MLG for certain airplanes until the replacement of the 
sidestay jack pivot assemblies with new, improved assemblies is 
accomplished. The proposed AD would expand the applicability of the 
existing AD to include additional airplanes. It also would require 
installation of new, improved sidestay jack pivot assemblies, which 
would constitute terminating action for the inspection requirements of 
this AD. The actions would be required to be accomplished in accordance 
with the service bulletins described previously.

Differences Between AD 94-26-12 and the Proposed Rule

    Operators should note that, although AD 94-26-12 permits continued 
flight with a single crack less than a certain length, and requires 
repetitive inspections not to exceed every 100 landings, this proposed 
AD would require that all cracked sidestay jack pivot assemblies be 
replaced with the new, improved assemblies within a specific amount of 
time. The maximum limits for cracking allowed, as recommended in the 
Beech (Raytheon) service bulletin (0.3 inch or 0.12 inch, depending on 
the crack location), are at the limits of what can be reliably detected 
using an ``on-airplane'' visual inspection procedure. The FAA finds 
that the safety implications and consequences associated with cracking 
of the sidestay jack pivot prohibit continued flight past 100 landings 
after the detection of any cracking. Additionally, the sidestay jack 
pivot assembly is easily replaced with the new, improved assembly, and 
the replacement will terminate the requirements for repetitive 
inspections of the existing sidestay jack pivot assemblies.

Clarification of Applicability

    Beech (Raytheon) Model BAe 125 series 800B and 1000B airplanes are 
similar in design to the airplanes affected by this proposed rule; 
however, those models have not yet been certificated for operation in 
the United States. Therefore, a note has been included in this proposed 
rule to clarify this and to suggest that airworthiness authorities of 
countries in which Model BAe series 800B and 1000B are approved for 
operation consider adopting corrective action that is similar to that 
proposed in this AD action.

Cost Impact

    There are approximately 550 Beech (Raytheon) Model BAe 125-1 
through 1000A series airplanes and Model Hawker 1000 airplanes of U.S. 
registry that would 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 on U.S. operators of the actions currently 
required is estimated to be $198,000, or $360 per airplane, per 
inspection cycle.
    The new (replacement) actions that are proposed in this AD action 
would take approximately 4 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts would cost 
approximately $1,200 per airplane. Based on these figures, the cost 
impact on U.S. operators of the proposed requirements of this AD 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 current or proposed 
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 proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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.

[[Page 54361]]

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), to read as follows:

Beech (Raytheon): 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 otherwise 
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: Beech (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 Beech (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 Beech (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 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 Beech (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 Beech (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 
(f)(1) or (f)(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

[[Page 54362]]

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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Manager, Standardization Branch.

    (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.

    Issued in Renton, Washington, on October 10, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-26710 Filed 10-17-96; 8:45 am]
BILLING CODE 4910-13-U