Document ID: FAA-2008-0556-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Various Aircraft Equipped With Honeywell Primus II RNZ 850( )/-851( ) Integrated Navigation Units
Posted Date: 2010-03-29T04:00Z

[Federal Register: March 29, 2010 (Volume 75, Number 59)]
[Rules and Regulations]               
[Page 15331-15336]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29mr10-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0556; Directorate Identifier 2007-NM-028-AD; 
Amendment 39-16246; AD 2010-07-02]
RIN 2120-AA64

 
Airworthiness Directives; Various Aircraft Equipped With 
Honeywell Primus II RNZ-850( )/-851( ) Integrated Navigation Units

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

[[Page 15332]]

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Honeywell Primus II RNZ-850( )/-851( ) 
integrated navigation units (INUs). As one alternative for compliance, 
the existing AD provides for a one-time inspection to determine whether 
a certain modification has been installed on the Honeywell Primus II 
NV-850 navigation receiver module (NRM), which is part of the INU. In 
lieu of accomplishing this inspection, and for aircraft found to have 
an affected NRM, that AD provides for revising the aircraft flight 
manual to include new limitations for instrument landing system 
approaches. That AD also requires an inspection to determine whether 
certain other modifications have been done on the NRM; and doing 
related investigative, corrective, and other specified actions, as 
applicable; as well as further modifications to address additional 
anomalies. This AD extends the compliance time for a certain inspection 
and associated actions. This AD also revises the applicability to 
include additional affected INUs. This AD results from reports 
indicating that erroneous localizer and glideslope indications have 
occurred on certain aircraft equipped with the subject INUs. We are 
issuing this AD to ensure that the flightcrew has accurate localizer 
and glideslope deviation indications. An erroneous localizer or 
glideslope deviation indication could lead to the aircraft making an 
approach off the localizer, which could result in impact with an 
obstacle or terrain.

DATES: This AD becomes effective May 3, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 3, 2010.
    On December 1, 2006 (71 FR 62907, October 27, 2006), the Director 
of the Federal Register approved the incorporation by reference of 
Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003; 
and Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004.

ADDRESSES: For service information identified in this AD, contact 
Honeywell Aerospace, Technical Publications and Distribution, M/S 2101-
201, P.O. Box 52170, Phoenix, Arizona 85072-2170; telephone 602-365-
5535; fax 602-365-5577; Internet http://www.honeywell.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Daniel Bui, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5339; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-22-05, Amendment 
39-14802 (71 FR 62907, October 27, 2006). The existing AD applies to 
various aircraft equipped with certain Honeywell Primus II RNZ-850( )/-
851( ) integrated navigation units (INUs). That NPRM was published in 
the Federal Register on May 19, 2008 (73 FR 28751). That NPRM proposed 
to continue to provide, as one alternative for compliance, a one-time 
inspection to determine whether a certain modification has been 
installed on the Honeywell Primus II NV-850 navigation receiver module 
(NRM), which is part of the INU. In lieu of accomplishing this 
inspection, and for aircraft found to have an affected NRM, that NPRM 
proposed to continue to provide for revising the aircraft flight manual 
to include new limitations for instrument landing system approaches. 
That NPRM proposed to continue to require an inspection to determine 
whether certain other modifications have been done on the NRM; and 
doing related investigative, corrective, and other specified actions, 
as applicable; as well as further modifications to address additional 
anomalies. That NPRM also proposed to extend the compliance time for a 
certain inspection and associated actions and to revise the 
applicability to include additional affected INUs.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request for Credit for Actions Performed in Compliance With Previous 
Service Information

    Two commenters, ExpressJet Airlines and Honeywell, request that 
credit be given for actions performed in compliance with previous 
service information.
    ExpressJet Airlines states that paragraph (l) of the NPRM calls for 
an inspection on any INU that is not identified in Table 2 of the NPRM. 
However, the NPRM does not take into account the units which have 
already been driven to Mod T status by Honeywell Service Bulletin 
7510100-34-0037, dated July 8, 2004. ExpressJet requests that 
compliance with Honeywell Service Bulletin 7510100-34-0037 be 
considered as an alternative to the inspections required in paragraph 
(l) of the NPRM.
    Honeywell also commented on the same issue. Honeywell states that 
it is concerned that many airplanes have been inspected and verified to 
be compliant with AD 2006-22-05. Honeywell asks the FAA to clarify 
whether the intent of the NPRM was to require that all affected 
operators re-inspect their airplanes. Honeywell also asks if the FAA 
can make a note under the compliance section to advise operators who 
actually complied with AD 2006-22-05 and verified their radios have 
modification AS and the new part number installed that they were 
already compliant with the new AD.
    We agree to provide clarification for both ExpressJet Airlines' and 
Honeywell's comments. Paragraph (l) of this AD applies only to any INUs 
that are not listed in Table 2 of this AD (which is the same list as 
Table 1 of AD 2006-22-05). In addition, if operators have previously 
inspected INUs that are not listed in Table 2 and have accomplished the 
applicable actions specified in paragraph (l) of this AD, then those 
operators are already in compliance with paragraph (l) of this AD. 
According to paragraph (e) of this AD, the actions are required within 
the specified compliance time, unless already accomplished. Honeywell 
Service Bulletin 7510100-34-0037 only addresses the localizer fix. 
However, this AD requires that the glide slope be fixed in addition to 
the localizer. We will not consider compliance with Honeywell Service 
Bulletin 7510100-34-0037 as an alternative to the inspections required 
in paragraph (l) of the NPRM. No changes have been made to the final 
rule.

[[Page 15333]]

Request To Remove Reference to Specific Revision of Service Information

    Honeywell requests that the FAA remove the reference to Revision 1, 
dated January 21, 2003, of the Honeywell Technical Newsletter (TNL) 
A23-3850-001 and simply reference the ``current revision.'' The TNL is 
currently at Revision 6. Based on the release of this new AD, Honeywell 
states that it plans to update the TNL with current information and 
clarify how to interpret the AD. Honeywell states that it cannot 
release the update until the new AD is released.
    We disagree with Honeywell's request to refer to the ``current 
revision'' of the TNL. The NPRM did not require the Honeywell TNL, but 
did require Honeywell Alert Service Bulletin 7510100-34-A0035, dated 
July 11, 2003; and Honeywell Service Bulletin 7510100-34-0037, dated 
July 8, 2004; as the appropriate sources of service information to 
accomplish the required actions in this AD. Honeywell provided the TNL 
as a tool to communicate with its customers regarding this technical 
issue. We included the TNL in Note 3 of the NPRM for reference only. To 
avoid confusion, we have removed Note 3 of the NPRM, which referred to 
this TNL.

Request To Revise Paragraph (j) of the NPRM

    Honeywell recommends wording changes to paragraph (j) of the NPRM 
to remove the sentence ``If Mod T is installed, no further action is 
required by this paragraph.''
    We agree to remove the sentence ``If Mod T is installed, no further 
action is required by this paragraph'' from paragraph (j) of the NPRM. 
Although Honeywell provides no justification for this wording change, 
we agree that making this change provides further clarification. Doing 
Mod T repairs only the localizer in accordance with Honeywell Service 
Bulletin 7510100-34-0037, dated July 8, 2004. However, the intent of 
this AD is to require that the glide slope and the localizer be 
serviced. Doing Mod T repairs the localizer in accordance with 
Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004. The 
glide slope is addressed by accomplishing the actions in Honeywell 
Alert Service Bulletin 7510100-34-A0034, dated February 28, 2003. 
Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 2003, 
does not address the localizer; it provides instructions for changing 
the part number after the glide slope is repaired. The glide slope and 
the localizer repairs are accomplished independent from each other in 
different Honeywell service bulletins.
    Therefore, we have revised paragraph (j) of this AD by adding the 
text ``* * * (which relates to the glide slope fix) * * *'' to the 
sentence that begins ``If Mod L, N, P, or R is installed * * *'' and 
adding ``if Mod T is not installed (which relates to the localizer 
fix), within 30 months after December 1, 2006, do all applicable 
related investigative, corrective, and other specified actions in 
accordance with the Accomplishment Instructions * * *'' in that same 
sentence (before ``Honeywell Service Bulletin 7510100-34-0037, dated 
July 8, 2004''). We made this change to clarify that Honeywell Service 
Bulletin 7510100-34-0037, dated July 8, 2004, addresses the localizer 
fix. This change does not increase the scope of this AD.

Request To Include Additional Service Information

    Honeywell requests that we add Honeywell Alert Service Bulletin 
7510134-34-A0017, dated July 11, 2003, to Table 1 in the NPRM.
    We agree to include Honeywell Alert Service Bulletin 7510134-34-
A0017, dated July 11, 2003, in Table 1 of this final rule to maintain 
consistency because the other service bulletins included in Table 1 of 
this AD were issued in pairs. Honeywell Alert Service Bulletin 7510100-
34-A0034, dated February 28, 2003, was paired with Honeywell Alert 
Service Bulletin 7510134-34-A0016, Revision 001, dated March 4, 2003. 
Honeywell Service Bulletin 7510100-34-0037, dated July 8, 2004, was 
paired with Honeywell Service Bulletin 7510134-34-0018, dated July 8, 
2004. Adding Honeywell Alert Service Bulletin 7510134-A0017, does not 
change any requirements of this AD, because Honeywell Alert Service 
Bulletin 7510134-34-A0017 is a prerequisite to Honeywell Alert Service 
Bulletin 7510100-34-A0035, dated July 11, 2003, and Honeywell Alert 
Service Bulletin 7510100-34-A0035 refers to Honeywell Alert Service 
Bulletin 7510134-34-A0017.
    We contacted Honeywell for more information about the technical 
content of Honeywell Alert Service Bulletin 7510134-34-A0017, dated 
July 11, 2003. Honeywell Alert Service Bulletin 7510100-34-A0035, dated 
July 11, 2003, references Honeywell Alert Service Bulletin 7510134-34-
A0017, dated July 11, 2003, as a source of service information on the 
new part numbers assigned after performing Honeywell Alert Service 
Bulletin 7510100-34-A0034, dated February 28, 2003. We have added 
Honeywell Alert Service Bulletin 7510134-34-A0017, dated July 11, 2003, 
to Table 1 of this AD. This does not increase the financial burden on 
operators, nor does it increase the scope of the AD.

Request To Add Part Numbers

    Honeywell requests that we revise paragraph (l) of the NPRM to list 
part numbers 7510134-611, -631, -701, and -731; which are parts of the 
Honeywell Primus II RNZ-850( )/-851( ) INU after modification; to the 
inspection to determine whether Mod L, N, P, R, or T is installed.
    We agree to provide clarification. We have revised paragraphs (l), 
(l)(1), (l)(2), and (l)(3) of this AD to specify the NRM part numbers 
7510134-611, -631, -701, and -731 instead of the modification level. 
Paragraphs (l)(1) and (l)(2) of this AD correctly specify which 
combination of part number and modification level meets the technical 
requirements of the modification. We have determined that these changes 
will neither increase the economic burden on any operator nor increase 
the scope of the AD.

Explanation of Changes to This AD

    We have changed the product identification line in the body of this 
AD to specify the design approval holder of the affected appliance 
rather than ``various aircraft.''

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Explanation of Change to Costs of Compliance

    After the NPRM was issued, we reviewed the figures we have used 
over the past several years to calculate AD costs to operators. To 
account for various inflationary costs in the airline industry, we find 
it necessary to increase the labor rate used in these calculations from 
$80 per work hour to $85 per work hour. The cost impact information, 
below, reflects this increase in the specified hourly labor rate.

Costs of Compliance

    There are about 3,063 aircraft of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to

[[Page 15334]]

comply with this AD. The manufacturer states that it will supply 
required parts to existing customers at no cost.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                        Average
                 Action                   Work hours   labor rate     Parts       Cost per    Number of U.S.-registered             Fleet cost
                                                        per hour                  aircraft            aircraft
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection for NRM modification level..            1          $85           $0          $85  Up to 1,500...............  Up to $127,500.
AFM revision...........................            1           85            0           85  Up to 1,500...............  Up to 127,500.
Modification (to Mod T configuration)..            1           85            0           85  Up to 1,500...............  Up to 127,500.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed actions 
specified in this final rule, and that no operator would accomplish 
those actions in the future if this AD were not adopted. We have been 
advised, however, that the actions have already been done on some 
affected airplanes. Therefore, the future economic cost impact of this 
rule on U.S. operators is expected to be less than the cost impact 
figures indicated above.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14802 (71 FR 62907, October 27, 2006) and by 
adding the following new airworthiness directive (AD):

2010-07-02 Honeywell, Inc.: Amendment 39-16246. Docket No. FAA-2008-
0556; Directorate Identifier 2007-NM-028-AD.

Effective Date

    (a) This AD becomes effective May 3, 2010.

Affected ADs

    (b) This AD supersedes AD 2006-22-05, Amendment 39-14802.

Applicability

    (c) This AD applies to various aircraft, certificated in any 
category, equipped with any Honeywell Primus II RNZ-850( )/-851( ) 
integrated navigation units (INUs) identified in a service bulletin 
identified in Table 1 of this AD. The aircraft include, but are not 
limited to, BAE Systems (Operations) Limited (Jetstream) Model 4101 
airplanes; Bombardier Model BD-700-1A10 airplanes; Bombardier Model 
CL-215-6B11 (CL-415 variant) airplanes; Cessna Model 560, 560XL, and 
650 airplanes; Dassault-Aviation Model Mystere-Falcon 50 airplanes; 
328 Support Services GmbH (Dornier) Model 328-100 and -300 
airplanes; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model 
EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, 
-145MP, and -145EP airplanes; Learjet Model 45 airplanes; Hawker 
Beechcraft Corporation Model Hawker 800XP and Hawker 1000 airplanes; 
and Sikorsky Model S-76A, S-76B, and S-76C aircraft.

             Table 1--Service Bulletins Affected by This AD
------------------------------------------------------------------------
 INUs listed in Honeywell--      Revision--             Dated--
------------------------------------------------------------------------
(1) Alert Service Bulletin    001............  March 4, 2003.
 7510134-34-A0016.
(2) Alert Service Bulletin    Original.......  July 11, 2003.
 7510134-34-A0017.
(3) Service Bulletin 7510134- Original.......  July 8, 2004.
 34-0018.
(4) Alert Service Bulletin    Original.......  February 28, 2003.
 7510100-34-A0034.
(5) Alert Service Bulletin    Original.......  July 11, 2003.
 7510100-34-A0035.
(6) Service Bulletin 7510100- Original.......  July 8, 2004.
 34-0037.
------------------------------------------------------------------------

[[Page 15335]]

    Note 1:  This AD applies to Honeywell Primus II RNZ-850( )/-851( 
) INUs installed on any aircraft, regardless of whether the aircraft 
has been otherwise modified, altered, or repaired in the area 
subject to the requirements of this AD. For aircraft 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 (o) 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.

Unsafe Condition

    (d) This AD results from reports indicating that erroneous 
localizer and glideslope indications have occurred on certain 
aircraft equipped with the subject INUs. We are issuing this AD to 
ensure that the flightcrew has accurate localizer and glideslope 
deviation indications. An erroneous localizer or glideslope 
deviation indication could lead to the aircraft making an approach 
off the localizer, which could result in impact with an obstacle or 
terrain.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 2006-22-05

Compliance Time for Action

    (f) For any INU identified in Table 2 of this AD: Within 5 days 
after March 11, 2003 (the effective date of AD 2003-04-06, Amendment 
39-13054, which was superseded by AD 2006-22-05), accomplish the 
requirements of either paragraph (g) or (h) of this AD. After 
December 1, 2006 (the effective date of AD 2006-22-05), only 
accomplishing the requirements of paragraph (g) of this AD is 
acceptable for compliance with this paragraph.

                Table 2--INUs Identified in AD 2006-22-05
------------------------------------------------------------------------

-------------------------------------------------------------------------
P/N 7510100-811 through 7510100-814
inclusive.
P/N 7510100-831 through 7510100-834
inclusive.
P/N 7510100-901 through 7510100-904
inclusive.
P/N 7510100-911 through 7510100-914
inclusive.
P/N 7510100-921 through 7510100-924
inclusive.
P/N 7510100-931 through 7510100-934
inclusive.
------------------------------------------------------------------------

Inspection To Determine Part Number

    (g) For any INU identified in Table 2 of this AD: Perform a one-
time general visual inspection of the modification plate for the 
Honeywell Primus II NV-850 Navigation Receiver Module (NRM); part 
number 7510134-811, -831, -901, or -931; which is part of the 
Honeywell Primus II RNZ-850( )/-851( ) INU; to determine if Mod L 
has been installed. The modification plate is located on the bottom 
of the Honeywell Primus II RNZ-850( )/-851( ) INU, is labeled NV-
850, and contains the part number and serial number for the 
Honeywell Primus II NV-850 NRM. If Mod T is installed, the letter 
will be blacked out. The Honeywell service bulletins listed in Table 
1 of this AD are acceptable sources of service information for the 
inspection required by this paragraph.
    (1) If Mod L is installed, before further flight, do paragraph 
(h) or (j) of this AD. After December 1, 2006, only accomplishment 
of paragraph (j) is acceptable for compliance with this paragraph.

    Note 2:  For the purposes of this AD, a general visual 
inspection is defined as: ``A visual examination of an interior or 
exterior area, installation, or assembly to detect obvious damage, 
failure, or irregularity. This level of inspection is made from 
within touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Aircraft Flight Manual (AFM) Revision

    (h) For aircraft having an INU identified in Table 2 of this AD: 
Revise the Limitations section of the AFM to include the following 
statements (which may be accomplished by inserting a copy of the AD 
into the AFM):

``FLIGHT LIMITATIONS

    When crossing the Outer Marker on glideslope, the altitude must 
be verified with the value on the published procedure.
    For aircraft with a single operating glideslope receiver, the 
approach may be flown using normal procedures no lower than 
Localizer Only Minimum Descent Altitude (MDA).
    For aircraft with two operating glideslope receivers, the 
aircraft may be flown to the published minimums for the approach 
using normal procedures if both glideslope receivers are tuned to 
the approach and both crew members are monitoring the approach using 
independent data and displays.''

Parts Installation

    (i) For aircraft having an INU identified in Table 2 of this AD: 
As of March 11, 2003, no person may install a Honeywell Primus II 
NV-850 NRM on which Mod L has been installed, on the Honeywell 
Primus II RNZ-850( )/-851( ) INU of any aircraft, unless paragraph 
(h) or (j) of this AD is accomplished. As of December 1, 2006, only 
accomplishment of paragraph (j) is acceptable for compliance with 
this paragraph.

Inspection To Determine Modification Level of NRM

    (j) For any INU identified in Table 2 of this AD on which Mod L 
was found to be installed during the inspection required by 
paragraph (g) of this AD, or for aircraft on which paragraph (h) of 
this AD was accomplished: Within 30 months after December 1, 2006, 
do an inspection of the modification plate on the Honeywell Primus 
II NV-850 NRM; part number 7510134-811, -831, -901, or -931; which 
is part of the Honeywell Primus II RNZ-850( )/-851( ) INU; to 
determine if Mod L, N, P, R, or T is installed. The modification 
plate located on the bottom of the Honeywell Primus II RNZ-850( )/-
851( ) INU is labeled NV-850, and contains the part number and 
serial number for the Honeywell Primus II NV-850 NRM. If Mod L, N, 
P, R, or T is installed, the corresponding letter on the 
modification plate will be blacked out. Honeywell Alert Service 
Bulletin 7510100-34-A0035, dated July 11, 2003; and Honeywell 
Service Bulletin 7510100-34-0037, dated July 8, 2004; are acceptable 
sources of service information for this inspection. If Mod L, N, P, 
or R is installed (which relates to the glide slope fix), within 30 
months after December 1, 2006, do all applicable related 
investigative, corrective, and other specified actions, in 
accordance with the Accomplishment Instructions of Honeywell Alert 
Service Bulletin 7510100-34-A0035, dated July 11, 2003; and if Mod T 
is not installed (which relates to the localizer fix), within 30 
months after December 1, 2006, do all applicable related 
investigative, corrective, and other specified actions, in 
accordance with the Accomplishment Instructions of Honeywell Service 
Bulletin 7510100-34-0037, dated July 8, 2004; to ensure that the NRM 
is at the Mod T configuration. Once the actions in this paragraph 
are completed, the AFM revision required by paragraph (h) of this AD 
may be removed from the AFM.
    (k) If the inspection specified in paragraph (j) of this AD is 
done within the compliance time specified in paragraph (f) of this 
AD, paragraph (g) of this AD does not need to be done.

New Requirements of This AD

Inspection To Determine Mod Level

    (l) For any INU that is not identified in Table 2 of this AD: 
Within 30 months after the effective date of this AD, perform a one-
time general visual inspection of the modification plate for the 
Honeywell Primus II NV-850 Navigation Receiver Module (NRM); part 
number 7510134-611, -631, -701, -731, 811, -831, -901, or -931; 
which is part of the Honeywell Primus II RNZ-850()/-851() INU; to 
determine whether Mod L, N, P, R, or T is installed. The 
modification plate located on the bottom of the Honeywell Primus II 
RNZ-850()/-851() INU is labeled NV-850, and contains the part number 
and serial number for the Honeywell Primus II NV-850 NRM. If Mod L, 
N, P, R, or T is installed, the corresponding letter on the 
modification plate will be blacked out. Honeywell Alert Service 
Bulletin 7510100-34-A0035, dated July 11, 2003; and Honeywell 
Service Bulletin 7510100-34-0037, dated July 8, 2004; are acceptable 
sources of service information for this inspection.
    (1) If the NRM is part number 7510134-611, -631, -701, or -731, 
and has Mod T

[[Page 15336]]

installed: No further action is required by this paragraph.
    (2) If the NRM is part number 7510134-611, -631, -701, or -731, 
and Mod T is not installed, within 30 months after the effective 
date of this AD: Do all applicable related investigative, 
corrective, and other specified actions, in accordance with the 
accomplishment Instructions of Honeywell Service Bulletin 7510100-
34-0037, dated July 8, 2004; to ensure that the NRM is at the Mod T 
configuration.
    (3) If the NRM is part number 7510134-811, -831, -901, or -931: 
Within 30 months after the effective date of this AD, do all 
applicable related investigative, corrective, and other specified 
actions, in accordance with the Accomplishment Instructions of 
Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 11, 
2003; and Honeywell Service Bulletin 7510100-34-0037, dated July 8, 
2004; to ensure that the NRM part number has been updated to 
7510134-611, -631, -701, -731 configuration and Mod T has been 
installed.

Parts Installation

    (m) As of the effective date of this AD, no person may install a 
Honeywell Primus II RNZ-850()/-851() INU that contains a NV-850 NRM 
part number 7510134-811, -831, -901, or -931; or part number 
7510134-611, -631, -701, or -731, that does not have Mod T 
installed, unless paragraph (l) is accomplished.

No Report

    (n) Where Honeywell Alert Service Bulletin 7510100-34-A0035, 
dated July 11, 2003 (or any of the related service information 
referenced therein), specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Daniel Bui, Aerospace Engineer, Systems and Equipment Branch, 
ANM-130L, FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5339; fax (562) 627-5210.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

Material Incorporated by Reference

    (p) You must use the service information contained in Table 3 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise. (Only the first page of these 
documents specifies the revision level of the document; no other 
page contains this information.)

             Table 3--All Material Incorporated by Reference
------------------------------------------------------------------------
         Honeywell--             Revision--             Dated--
------------------------------------------------------------------------
Alert Service Bulletin        001............  March 4, 2003.
 7510134-34-A0016
Alert Service Bulletin        Original.......  July 11, 2003.
 7510134-34-A0017
Alert Service Bulletin        Original.......  February 28, 2003.
 7510100-34-A0034
Alert Service Bulletin        Original.......  July 11, 2003.
 7510100-34-A0035
Service Bulletin 7510100-34-  Original.......  July 8, 2004.
 0037
Service Bulletin 7510134-34-  Original.......  July 8, 2004.
 0018
------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

             Table 4--New Material Incorporated by Reference
------------------------------------------------------------------------
         Honeywell--             Revision--             Dated--
------------------------------------------------------------------------
Alert Service Bulletin        001............  March 4, 2003.
 7510134-34-A0016
Alert Service Bulletin        Original.......  July 11, 2003.
 7510134-34-A0017
Alert Service Bulletin        Original.......  February 28, 2003.
 7510100-34-A0034
Service Bulletin 7510134-34-  Original.......  July 8, 2004.
 0018
------------------------------------------------------------------------

    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Honeywell Alert Service Bulletin 
7510100-34-A0035, dated July 11, 2003; and Honeywell Service 
Bulletin 7510100-34-0037, dated July 8, 2004; on December 1, 2006 
(71 FR 62907, October 27, 2006).
    (3) For service information identified in this AD, contact 
Honeywell Technical Operations Center, 1944 East Sky Harbor Circle, 
Phoenix, AZ 85034-3442; telephone (US & Canada) 800-601-3099, 
(International) 602-365-3099; Internet http://www.honeywell.com.
    (4) You may review copies of the service information at the 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on March 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-6547 Filed 3-26-10; 8:45 am]
BILLING CODE 4910-13-P